text: National Advisory Committee for Aeronautics N0.93 R esearc h Abstracts NOVEMBER 30 CURRENT NACA REPORTS NACA RM E55B11 FULL-SCALE PERFORMANCE STUDY OF A PRO- TOTYPE CRASH-FIRE PROTECTION SYSTEM FOR RECIPROCATING-ENGINE-POWERED AIRPLANES. Dugald O. Black and Jacob C. Moser. November 1955. 36p. diagrs., photos. (NACA RM E55B11) An airplane was experimentally crashed to study the performance of a prototype crash-fire inerting sys- tem for reciprocating-engine-powered airplanes. The results of previous experimental crashes indi- cate that the crash conditions imposed almost always result in fire. The inerting system was therefore exposed to conditions that would adequately test its ability to inert and de-energize the various ignition sources known to cause crash fires. The fact that fire did not occur during this crash indicated that the crash-fire inerting system functioned satisfactorily as a complete unit. The prototype inerting system functioned with a rapidity equal to or greater than that of the experimental system used in the NACA crash-fire studies. NACA RM E55H11 A SURVEY OF UNCLASSIFIED AXIAL -FLOW- COMPRESSOR LITERATURE. Howard Z. Herzig and Arthur G. Hansen. November 1955. i, 88p. (NACA RM E55H11) A survey of unclassified axial-flow-compressor literature is presented in the form of brief reviews of the methods, results, and conclusions of selected reports. The reports are organized into several main categories with subdivisions, and frequent ref- erences are made within the individual reviews to pertinent material elsewhere in the survey. NACA RM E55127a AVERAGE BOND ENERGIES BETWEEN BORON AND ELEMENTS OF THE FOURTH, FIFTH, SIXTH, AND SEVENTH GROUPS OF THE PERIODIC TABLE. Aubrey P. AltshuUer. November 1955. 7p. tab. (NACA RM E55I27a) The average bond energies D (B-Z) for boron- containing molecules have been calculated by the Pauling geometric-mean equation. These calculated bond energies are compared with the average bond energies Dg (B-Z) obtained from experimental data. Thehigher values of Dgxp(B-Z) in compar- ison with lUijj(B-Z) when Z is an element in the fifth, sixth, or seventh periodic group may be attrib- uted to resonance stabilization or double-bond char- acter. NACA TM 1384 METALLOGRAPHY OF ALUMINUM ANIVITi ALLOYS. USE OF ELECTROLYTIC POLiSH (Metallographie de I'aluminium et de ses alHages^ Emploi du polissage electrolytique). P. A. Jafrquet. November 1955. ii, BOp. diagrs., photos., tabs. " (NACA TM 1384. Trans, from Office National d'Etudes et de Recherches Aeronautiques, Pub. 51, 1952) Recent methods are described for electropolishing aluminum and aluminum alloys. Numerous refer- ences are included of electrolytic micrographic investigations carried out during the period 1948 to 1952. A detailed description-af a commercial elg§-' trolytic polishing unit, suitable for micrographic Ex- amination of aluminum and its alloys, is included. NACA TN 3413 INVESTIGATION OF THE tJSfiOF A RUBBER ANA- LOG IN THE STUDY OF STRESS DISTRIBUTION IN RIVETED AND CEMENTED JOINTS. Louis R. Demarkles, Massachusetts Institute of Technology. November 1955. 97p. diagrs., tabs. (NACA TN 3413) Results are presented of an investigation made to study the stress distribution within cemented and riveted joints by use of an analogous joint con- structed of a highly flexible material. Displacement measurements obtained from foam-rubber analogs, and rational though not rigorously sound formulas for shear stress distribution in joints, are given. NACA TN 3469 SUMMARY OF RESULTS OBTAINED BY TRANSONIC-BUMP METHOD ON EFFECTS OF PLAN FORM AND THICKNESS ON LIFT AND DRAG CHARACTERISTICS OF WINGS AT TRANSONIC SPEEDS. Edward C. Polhamus. November 1955. 33p. diagrs., tab. (NACA TN 3469. Supersedes RM L51H30) This paper presents a summary of the effects of plan form and thickness on the lift and drag charac- teristics of wings at transonic speeds and compari- sons with subsonic, transonic, and supersonic theories. The data considered in this summary were obtained during a transonic research program con- ducted in the Langley high-speed 7- by 10-foot tunnel by the transonic-bump method. The Reynolds num- bers of the tests were generally less than 1 x 10^. I I U.S. DEPOWT OBtV f II 11 ■■■ HIT" •AVAILABLE ON LOAN ONLY. ADDRESS REQUESTS FOR DOCUMENTS TO NACA, 15H H ST., NW., WASHINGTON 25, D C, CITING CODE NUMBER ABOVE EACH TITLE; THE REPORT TITLE AND AUTHOR. NACA TN 3492 DETERMINATION OF INFLOW DISTRIBUTIONS FROM EXPERIMENTAL AERODYNAMIC LOADING AND BLADE-MOTION DATA ON A MODEL HELI- COPTER ROTOR IN HOVERING AND FORWARD FLIGHT. Gaetano Falabella, Jr., and John R. Meyer, Jr.. Massachusetts Institute of Technology. November 1955. 184p. diagrs., photos., tab. (NACA TN 3492) Inflow distributions, azimuth and spanwise, were determined analytically from measured pressure distributions and blade-motion data on a model heli- copter rotor blade under hovering and simulated forward-flight conditions. Pressures and corre- sponding blade flapping were recorded for various rotor conditions at tip-speed ratios of 0.10 to 1.00. Supplementary information concerning reverse-flow effects on offset -blade motion, measured forces and moments on a typical offset model rotor, and addi- tional recorded pressure data are also included. NACA TN 3524 THE EFFECT OF REYNOLDS NUMBER ON THE STALLING CHARACTERISTICS AND PRESSURE DISTRIBUTIONS OF FOUR MODERATELY THIN AIRFOIL SECTIONS. George B. McCuUough. November 1955. 24p. diagrs., tabs. (NACA TN 3524) Low-speed measurements of the lift, drag, pitching moment, and pressure distribution of the NACA 0008, 0007.5, 0007, and 0006 airfoil sections are presented for Reynolds numbers from 1.5 to 6 mil- lion. It is shown that the flow over these sections underwent a change at some value of the lift coeffi- cient which depended on the airfoil thickness ratio and Reynolds number. The effect of the flow change on maximum lift was small. NACA TN 3525 VORTEX INTERFERENCE ON SLENDER AIR- PLANES. Alvin H. Sacks. November 1955. diagr. (NACA TN 3525) 19p. Formulas are developed for the forces and moments due to vortex interference on a slender wing-body- tail combination of general cross section performing quasi-stationary maneuvers. It is found that in steady straight flight the interference lift depends only on the impulse of each shed vortex and its image vortex in a transformed circle plane, this quantity to be determined at the wing trailing edge and at the base of the configuration. NACA RESEARCH ABSTRACTS NO. 93 NACA TN 3526 FLIGHT CALIBRATION OF FOUR AIRSPEED SYS- TEMS ON A SWEPT-WING AIRPLANE AT MACH NUMBERS UP TO 1.04 BY THE NACA RADAR- PHOTOTHEODOLITE METHOD. Jim Rogers Thompson, Richards. Bray, and George E . Cooper. November 1955. 41p. diagrs., photos., tab. (NACA TN 3526. Supersedes RM A50H24) The characteristics of four different airspeed sys- tems installed in a swept-wing airplane have been investigated in flight up to 1.04 Mach number by the NACA radar-phototheodolite method of airspeed calibration. The variations of static-pressure de- fect per unit indicated impact pressure with Mach number and a limited amount of information on the effect of airplane normal-force coefficient are pre- sented for each system. The results are compared with available theory and wind-tunnel tests of the isolated heads. NACA TN 3547 AERODYNAMIC CHARACTERISTICS OF A SMALL- SCALE SHROUDED PROPELLER AT ANGLES OF ATTACK FROM 0° TO 90°. Lysle P. Parlett. November 1955. 12p. diagrs. (NACA TN 3547) Tests have been performed to determine the effects of airspeed and angle of attack on the lift, drag, and pitching moment of a shrouded-propeller model, having a shroud length of about two-thirds of the propeller diameter, over an angle-of-attack range from 0° to 90°. Tests were made of the complete model with the propeller operating and also of the shroud alone with the propeller removed. The effect of inlet-lip cross-sectional radius on the static- thrust characteristics was also studied. NACA TN 3548 FLIGHT INVESTIGATION AT MACH NUMBERS FROM 0.6 TO 1.7 TO DETERMINE DRAG AND BASE PRESSURES ON A BLUNT-TRAILING-EDGE AIRFOIL AND DRAG OF DIAMOND AND CIRCULAR- ARC AIRFOILS AT ZERO LIFT. John D. Morrow and Ellis Katz. November 1955. 19p. diagrs., photos. (NACA TN 3548. Supersedes RM L50E19a) Results of an exploratory free-flight investigation at zero lift of several rocket-powered drag-research models having rectangular 6-percent -thick wings are presented for a Mach number range of 0.6 to 1.7. Wings having diamond, circular-arc, and blunt- trailing-edge airfoil sections were tested. Pres- sures over the base of the blunt -trailing-edge airfoil were measured. The drags of all the models were measured and are compared with theory in this paper. NACA RESEARCH ABSTRACTS NO. 93 NACA TN 3569 COMPRESSIBLE LAMINAR BOUNDARY LAYER AND HEAT TRANSFER FOR UNSTEADY MOTIONS OF A FLAT PLATE. Simon Ostrach. November 1955. 26p. diagrs., tab. (NACA TN 3569) The laminar compressible boundary layer and heat transfer over an isothermal semi-infinite flat plate moving with a time-dependent velocity has been ana- lyzed. First-order deviations from the quasi- steady velocity and temperature profiles and boundary-layer characteristics have been computed. A plate oscillating about a steady velocity is consid- ered as an example. NACA TN 3574 ACOUSTIC ANALYSIS OF RAM-JET BUZZ. Harold Mirels. November 1955. 33p diagrs. (NACA TN 3574) A one-dimensional analysis of ram-jet buzz is pre- sented. It is assumed that the buzz has a linear instability origin and that the combustion chamber is of constant area. The configuration is shown to be unstable when the real part of the acoustic impedance of the inlet is greater than a term of the order of the combustion-chamber Mach number. Computations indicate that burning with a fixed planar flame front and constant heat release per unit mass increases the stable operating range. NACA TN 3583 CHARTS OF BOUNDARY-LAYER MASS FLOW AND MOMENTUM FOR INLET PERFORMANCE ANALY- SIS MACH NUMBER RANGE. 0.2 TO 5.0. Paul C. Simon and Kenneth L. Kowalski. November 1955. 32p. diagrs., tab. (NACA TN 3583) Significant flow parameters for various fractions of a turbulent boundary layer are presented in chart form for a number of power-law velocity profiles and a range of Mach numbers up to 5.0. Estimates of auxiliary inlet mass flow or momentum may easily be made. Application of the charts to inlets of arbitrary shape and to the determination of the pres- sure recovery of rectangular normal-shock inlets immersed in boundary layer is described. NACA TN 3586 IMPINGEMENT OF WATER DROPLETS ON NACA 65A004 AIRFOIL AT 0° ANGLE OF ATTACK. Rinaldo J. Brun and Dorothea E. Vogt. November 1955. 28p. diagrs. (NACA TN 3586) The trajectories of droplets in the air [lowing past an NACA 65A004 airfoil at an angle of attack of 0° were determined. The amount of water in droplet form impinging on the airfoil, the area of droplet impingement, and the rate of droplet impingement per unit area on the airfoil surface were calculated from the trajectories and presented to cover a large range of flight and atmospheric conditions. These impingement characteristics are compared briefly with those previously reported for the same airfoil at angles of attack of 4° and 8°. BRITISH REPORTS N-40040* National Gas Turbine Establishment (Gt. Brit.) AN EXPERIMENTAL INTRODUCTION TO THE JET FLAP; N. A. Dimmock. July 1955. 68p. diagrs., photos., tabs. (NGTE R. 175) Results are given of two airfoils, each having 12.5- percent-thick elliptical cross section with a narrow full-span jet slot at the trailing edge, the jet deflec- tions being, respectively, 90° and 31.4°. The val- ues of the force and moment coefficients and deriv- atives agree with those suggested by theory in a pre- vious report. Support is given to the thrust hypoth- esis in that the measured thrust was greater, under appropriate conditions, than the reaction component from the deflected jet. The losses in the system are considered and some are investigated, those due to Reynolds number and jet entrainment effects being included. Influence of ground on lift and center of lift was measured and found not to be prohibitive. N-40048 Royal Aircraft Establishment (Gt. Brit. ) TESTS OF HUMIDITY EFFECTS ON FLOW IN A WIND TUNNEL AT MACH NUMBERS BETWEEN 2.48 AND 4. R. J. Monaghan. January 1955. 33p. diagrs. (RAE Tech. Note Aero 2358) Static and pilot pressure distributions were meas- ured in the working section of a 5-in. by 5-in. supersonic wind tunnel at nominal Mach numbers of 2.48, 3.25, and 4, over ranges of absolute humidity at the inlet from 5 x 10"^ to 3 x 10'^. Previous work indicates that a condensation shock would occur in the nozzle. For a stagnation pressure of 1 at- mosphere and stagnation temperatures giving zero heat-transfer conditions at the walls, no humidity effects were discernible if the absolute humidity was less than 2 x 10"^ at M = 2.48, 3 x 10"* at M = 3.12, and about 5 x 10"* at M = 3.8. N-40068 Aeronautical Research Council (Gt. Brit.) TESTS ON A SWEPT-BACK WING AND BODY WITH ENDPLATES AND WING TIP TANKS IN THE COM- PRESSED AIR TUNNEL. C. Salter and R. Jones. APPENDIX - COMPARISON BETWEEN THE MEAS- URED LIFT AND DRAG AND CALCULATED VAL- UES FOR THE WING WITH TIP TANKS. J. Weber. 1954. 26p. diagrs.. tabs. (ARC CP 196) Results are given of experiments to determine the effect on lift, drag and pitching moment, of wing tip tanks and of two sizes of end plates on a tapered swept wing model. The tests were undertaken pri- marily to extend the range of Reynolds number for checks on previous theoretical work. As regards lift and pitching moment, the effects are found to be fairly well defined. The drag characteristics are less consistent, but it seems that end plates have the effect of reducing the drag of the model over quite a large range of C^- This does not apply in the case of the wing lip tanks. N-40069' Aeronautical Research Council (Gt. Brit. ) WIDE RANGE AMPLIFIER FOR TURBULENCE MEASUREMENTS WITH ADJUSTABLE UPPER FREQUENCY LIMIT. H. Schuh and D. Walker. 1955. 42p. diagrs. (ARC CP 198) Requirements are discussed for an amplifier suit- able for subsonic and supersonic turbulence work with hot wires. An amplifier is described which has a frequency range from 1.4 c/s to 50 kc/s, dealing with a range of thermal time lag from 0.1 m. s. to 5 m. s. An iron dust-cored inductance is used to give the required compensation for thermal lag, the circuit being a modification of Dryden's circuit. The upper frequency cutoff is adjustable in six steps from 1.5 kc/s to 50 kc/s. The output can be applied to a thermocouple meter and to an oscilloscope. N-40080'' Aeronautical Research Council (Gt. Brit. ) FLIGHT TESTS AT TRANSONIC SPEEDS ON FREE- LY FALLING MODELS. PARTS I TO V. Edited by C. Kell. PART I - HISTORICAL. C. Kell. PART n - EQUIPMENT AND TECHNIQUE. C. Kell and J. Swan. PART III -DRAG EXPERIMENTS. C. Kell and F. Smith. PART IV - FLUTTER EX- PERIMENTS. W. G. Molyneux and E. W. Chappie. PART V - NOTES ON THE ACCURACY OF THE FREELY FALLING MODEL EXPERIMENT. T. F. C. Lawrence. 1955. 32p. diagrs., photos., tab. (ARC R fe M 2902. Supersedes RAE Tech. Memo. Aero 308) Basic bodies carrying the airfoils to be tested were released from an aircraft flying at height, and accel- erated under the influence of gravity through the transonic speed range. Radar recorded the flight path and telemetering equipment carried within the body transmitted information to a ground station during the free fall. This work started in 1943 and was brought to a close in 1949. N-40082* Aeronautical Research Council (Gt. Brit.) OBSERVATIONS OF THE FLOW ROUND A TWO- DIMENSIONAL AEROFOIL OSCILLATING IN A HIGH-SPEED AIR STREAM. A. Chinneck, D. W. Holder, and C. J. Berry. 1955. 18p. diagrs., photos., tab, (ARC R i: M 2931. Supersedes ARC 15. 141; FM 1779 & 0.1006) Photographs have been taken of the flow around a 10-percent-thick RAE 104 airfoil performing pitch- ing oscillations at low values of the frequency pa- rameter in subsonic and supersonic airstreams. Apart from a difference of phase, the general flow pattern appeared to be similar to those observed in steady motion, the pattern for a particular instanta- neous incidence of the oscillation resembling that for steady motion at a different incidence. It is suggested that, for the range of frequency parameter covered, the observed phase lag of the flow pattern corresponds to the lag in the circulation. NACA RESEARCH ABSTRACTS NO. 93 N-40084 Aeronautical Research Council (Gt. Brit.) THE AERODYNAMIC EFFECTS OF ASPECT RATIO ON FLUTTER OF UNSWEPT WINGS. W. G. Molyneux and E. W. Chappie. 1955. 12p. diagrs., tab. (ARC R S; M 2942; 15,609. Supersedes RAe' Structures 135) A method is described for the direct measurement o£ the aerodynamic effects of aspect ratio on wing flut- ter. The method requires the use of stiff (virtually rigid) wings fle.xibly mounted at the root. Details are given of tests on untapered, unswept wings with freedoms in modes of linear flexure and uniform pitch. A comparison is made between measured values of the flutter characteristics and the values calculated using an aerodynamic theory for oscil- lating wings of finite aspect ratio, and reasonable agreement for flutter speeds and frequencies is obtained. N-40186* Royal Aircraft Establishment (Gt. Brit.) MEASUREMENTS OF PITCHING MOMENT DERIVA- TIVES FOR A SERIES OF RECTANGULAR WINGS AT LOW WIND SPEEDS. P. R. Guyett and D. E. G. Poulter. June 1955. 52p. diagrs., tabs. (RAE Structures 185) The direct aerodynamic moments for pitching oscil- lations have been measured on a series of rectangu- lar wings having aspect ratios between 2 and 8 for axis positions at the wing leading edges and trailing edges. Two of the wings were also tested with single end plates which were aerodyna.mically effec- tive in doubling the wing geometric aspect ratio. The measurements were made at low speeds in an open jet wind tunnel ajid covered the range of fre- quency parameter (based on wing chord) 0.13 to 0.39. The results are in general agreement with theoreti- cal results due to Lawrence and Gerber. Similar tests were also made on a wing fitted with two end plates in an attempt to obtain results for two- dimensional flow. The results do not agree with other experimental results and two-dimensional theoretical values and indicate that wind-tunnel in- terference is important for this test configuration. N-40187 Royal Aircraft Establishment (Gt. Brit.) THE MECHANICAL PROPERTIES AND STRUCTURE OF CONTINUOUSLY CAST A.C.9 ALUMINIUM ALLOY TUBES. P. C. Bradley and D. Bunting. June 1955. lOp. diagr., photos., labs. (RAE Tech. Note RPD 122) The mechanical properties of a large diameter tube continuously cast in aluminum alloy A.C. 9 have been investigated at room and at elevated temperature, in connection with the use of such tubes as fuel or oxidant tanks for rocket motors. The variation in structure of the alloy across a section is described and discussed with reference to the possible detri- mental effect of primary silicon crystals on the mechanical properties. The operating temperature should not be allowed to exceed about 180° C if tanks of this material are to be used more than once. NACA RESEARCH ABSTRACTS NO. 93 N-40188'' Royal Aircraft Establishment (Gt. Brit.) THE EFFECTS OF TAPER ON THE SUPERVELOC- ITIES ON THREE-DIMENSIONAL WINGS AT ZERO INCIDENCE. K. W. Newby. June 1955. 120p. diagrs., tab. (RAE Aero 2544) Relationships have been derived for expressing the velocities on three-dimensional tapered wings at zero incidence in terms of the velocities on un- tapered infinite swept wings. The theoretical inves- tigation of the effects of taper is confined to simple wings having airfoil sections formed by cubic or parabolic arcs; some exj^erimental evidence is given to show that the results of this investigation can probably be applied quantitatively to wings having conventional airfoil sections. The results given in this report show that plan form and thickness taper have a marked effect on the velocities near the cen- ter of a wing, but that these effects decrease with in- crease of sweepback. A calculation method is out- lined in section 4.26 of the text for applying the re- sults obtained for wings having parabolic arc airfoil sections, to wings having arbitrary section shapes. N-40189* Royal Aircraft Estaclishment (Gt. Brit.) RECORDING AND PROCESSING FLIGHT TEST DATA BY DIGITAL METHODS. E. J. Petherick. (Prepared for AGARD Flight Test Panel). April 1955. 12p. photos. (RAE Tech. Note MS 20) This note reviews current developments in the re- cording and processing of flight test data by digital methods. It first describes four assessors which facilitate conversion of strip chart and kinetheodolite records to typewritten or punched card form. It then details some coded scales which can be read automatically, and finally it describes the incorpora- tion and use of such scales in a digital recording system intended for airborne use. N-40190* Royal Aircraft Establishment (Gt. Brit.) WIND TUNNEL TESTS ON A 6 FT DIAMETER HEL- ICOPTER ROTOR. T. B. Owen, R. A. Fail, and R. C. W. Eyre. May 1955. 33p. diagrs., tabs. (RAE Tech. Note Aero 2378) Thrust, torque, and flapping angle have been meas- ured on a 6-foot diameter rotor over a range of blade angle, shaft inclination, and tip speed ratio for comparison with the 12-foot diameter rotor previ- ously tested in the 24-foot tunnel. In addition to tests in the 24-foot tunnel, the 6-foot diameter rotor was also tested in the No. 2 11-1/2 foot tunnel to investigate tunnel constraint. Brief investigations were made of support interference and blade twist- ing. There are small discrepancies both as regards tunnel corrections and as regards the comparison of the 6-foot and 12-foot diameter rotors in the un- stalled operating range. Possible reasons are dis- cussed but small unexplained discrepancies remain. Blade stalling has larger effects on the 6- foot diam- eter rotor but owing to the progressive nature of the phenomenon it is not possible to define any precise limits to the ranges of validity of the results on the two rotors. N-40191* Aeroplane and Armament Experimental Establish- ment (Gt. Brit.) AN EXPERIMENTAL INVESTIGA- TION INTO THE PERFORMANCE OF A HELICOP- TER FOLLOWING SUDDEN REDUCTION IN POWER. G. W. Langdon. August 4, 1955. 12p. diagrs. (AAEE/Res/289). The performance of a single rotor helicopter fitted with a throttle override has been measured under conditions simulating the failure of one engine of a multiengined helicopter during take-off. Records of the motion are included and the experimental results are compared with theoretical predictions. N-40192 Royal Aircraft Establishment (Gt. Brit.) INVESTIGATION OF THE FATIGUE OF EXTRUDED TUBULAR BOOMS. W. A. P. Fisher and H. Yeomans. June 1955. 15p. diagrs., photos., tabs. (RAE Tech. Note Structures 162). The presence of the unmachined extruded surface of the bore in the tubes, as used for the "Viking" and "Valetta" spar booms, has a marked adverse effect on the basic fatigue strength of the tube. The fail- ures of the necked specimens show that the flaws at the inner surface are a source of fatigue. Scatter in the endurance of tubular spar booms is probably largely due to the chances of such flaws occurring at the side of a transverse hole. The specimens were made from aluminum alloy extruded tube DTD 364. N-40193* Marine Aircraft Experimental Establishment. (Gt. Brit.) INVESTIGATION OF HIGH LENGTH BEAM RATIO SEAPLANE HULLS WITH HIGH BEAM LOADINGS - HYDRODYNAMIC STABILITY. PART 17 - THE STABILITY AND SPRAY CHARAC- TERISTICS OF MODEL M. J. K. Fris\vell, D. M. Ridland, and A. G. Kurn. April 1955. 24p. diagrs., photos., tabs. (MAEE F Res 253) In this report results are presented of limited tests on the hydrodynamic characteristics of model M of the series, tliese tests being designed solely to pro- vide information on the interactions of the different relevant parameters. The model has a length-to- beam ratio of 13 (the forebody being 6 beams in length and the afterbody 7 beams), no forebody warp, an afterbody to forebody keel angle of 8'^, and a straight transverse step with a step depth of 0.15 beams. The tests comprised the determination of longitudinal stability limits without slipstream at C. =2.75 and an investigation of spray at this load- "o ing. A short discussion of the results is also included. N-40197* Royal Aircraft Establishment (Gt. Brit.) CORRELATED FATIGUE DATA FOR AIRCRAFT STRUCTURAL JOINTS. R. B. Heywood. June 1955. 16p. diagrs., tab. (RAE Structures 184) Results of fatigue tests carried out at RAE on typi- cal aircraft wing structural joints are correlated to give an indication of general fatigue behavior. The results are plotted in the form of S - Log N curves, and these indicate that the mode of behavior cannot be attributed to any single factor, such as the type of aluminum alloy, the ultimate tensile strength, or the mean stress of the fatigue cycle. The detailed meth- od of design undoubtedly has a predominant influence on behavior, but this quality is not revealed by a broad classification according to the proportion of load transmitted at holes. N-40198* Royal Aircraft Establishment (Gt. Brit.) A TECHNIQUE FOR THE MEASUREMENT OF PRESSURE DISTRIBUTION ON OSCILLATING AEROFOILS, WITH RESULTS FOR A RECTANGU- LAR WING OF ASPECT RATIO 3.3. W. G. Molyneux and F. Ruddlesden. June 1955. 24p. diagrs., tabs. (RAE Tech. Note Structures 164) Details are given of a strain-gage pressure trans- ducer that has been developed for measurements of pressure distribution on oscillating airfoils in low speed wind tunnels. The transducer characteristics are shown to be well suited to oscillatory measure- ments, and in particular the transducer output can be measured directly on a sensitive galvanometer with- out the need for preamplification. As an illustration of the use of the transducer, pressure measurements have been made in the RAE 5 -foot diameter open jet wind tunnel on a rectangular wing of aspect ratio 3.3 oscillating in modes of pitch and roll. Values for the aerodynamic derivatives have been obtained from the integrated pressure distributions, and are com- pared with those derived from overall force meas- urements and with theoretical values. The measured values are in close agreement but there are some discrepancies with theory that are thought to be due to a wind-tunnel interference effect. N-40199* Royal Aircraft Establishment (Gt. Brit.) THE INFLUENCE OF PRE-LOADING ON THE FA- TIGUE LIFE OF AIRCRAFT COMPONENTS AND STRUCTURES. R. B. Heywood. June 1955. 27p. diagrs., photos., tabs. (RAE Structures 182) Tests on aircraft components and structures are described which show that preloading can have a NACA RESEARCH ABSTRACTS NO. 93 marked influence on fatigue behavior. Tensile pre- loading may increase the life - in one instance a hundredfold improvement was obtained - and com- pressive preloading may reduce the life. The effect is attributed to residual stresses and to load re- distributions induced by preloading. N-40205* Ministry of Supply (Gt. Brit.) AN ABSORPTIOMETRIC METHOD FOR THE DE- TERMINATION OF CHROMIUM IN METHACRYLATO-CHROMIUM TREATED GLASS FABRIC. E. J. McLauchlan. August 1955. 4p. diagr. (MOS AID Chem. 6) An absorptiometric method for the determination of chromium in methacrylato-chromium treated glass fabric is described. A wet-oxidation attack is uti- lized to remove the chromium from the glass fibers and to oxidize the tervalent chromium to sexavalent chromium for subsequent absorptiometric deter- mination as the diphenylcarbazide complex. N-40207* Royal Aircraft Establishment (Gt. Brit.) OPTIMUM DESIGNS FOR REINFORCED CIRCULAR HOLES. E. H. Mansfield. June 1955. 26p. diagrs. (RAE Structures 183) The design of reinforced circidar holes in an Infinite sheet is considered theoretically. The stress sys- tem in the main body of the sheet is assumed to be one in which the principal stresses are in the ratio 1:-1 (that is, shear), 1:0 (that is, tension), 1:1 or 1:1 '2. The reinforcement may vary round the hole and families of such reinforcements with constant total weight are considered; the peak stresses in the sheet are evaluated so that optimum weight -strength designs are determined. N-40209 Royal Aircraft Establishment (Gt. Brit.) STATIC ELECTRICITY EN AIRCRAFT FUEL TANKS. F. L. Holmes and D. T. Sharwood. May 1955. lOp. diagrs., tab. (RAE Tech. Note EL. 82; Tech. Note Mech. Eng. 201) Tests were made to measure the static field strength generated in aircraft fuel tanks by foaming of the fuel. A type of apparatus for measuring static field strength is described with details of its application to these tests. The results show that the field strength is less than 1 volt per centimeter which is many times less than that required for flashover and the ignition of a fuel vapor/ air mixture. NACA RESEARCH ABSTRACTS NO. 93 UNPUBLISHED PAPERS N-22024* FLOW NEAR A HEATED SOLID BODY IN A STAND- ING ACOUSTIC WAVE. P. N. Kubanskii. October 1955. Up. diagrs. (Trans, of Zhurnal Tekhnich- eskoi Fiziki, v. 22, no. 4, April 1952, p. 585-592) Results of experiments carried out in standing waves generated by vibrations of finite amplitude are pre- sented. Two types of waves are considered; (1) forced standing waves, formed wtien the frequen- cy of outside vibrations does not correspond with the natural frequency of vibration of the radiating sys- tem, and (2) standing waves which form as the re- sult of coincidence of frequency of outside vibration with natural frequency of vibration of the radiating system. Optical methods are used in the examina- tion of the flow and the presence of higher harmonics in the standing acoustical wave is observed. The deformation of the waves is also studied. N-34452 SOFT ROT. DESTRUCTION OF WOOD THROUGH COMMON FUNGI. (Moderfaule. Die Zersetzung von Holz durch niedere Pilze). W. P. K. Findlay and J. G. Savory. October 1955. 12p. photos., tab. (Trans, from Holz als Roh- und Werkstoff, v. 12, no.8, August 1954, p. 293-296). If wood is exposed to humid weather for some length of time, a softening of the surface takes place which is due to a fungus attack. This phenomenon is of minor significance except in the case of cooling towers and similar Industrial water-cooling plants. Soft rot, as this fungus is generally called, was pro- duced according to a method by Abrams. The fungi causing soft rot are reviewed and preservatives for protection of wood are discussed, but further inves- tigations are required in order to indicate effective methods of protection of wood from soft rot. N-39717'' EFFECT OF ACOUSTICAL VIBRATIONS OF FINITE AMPLITUDE ON THE BOUNDARY LAYER. P. N. Kubanskii. October 1955. lip. diagrs. (Trans, of Zhurnal Tekhnicheskoi Fiziki, v. 22, no. 4, April 1952, p.593-601) It is concluded that acoustical standing waves of finite amplitude can produce currents near the wall of a solid body, even when the body is located in a stream. A considerable intensity of acoustical vibration is necessary in order to produce acoustical flow near the walls of a solid body in a stream. The acoustical streams produced near the walls of solid bodies exert an influence on the boundary layer which surrounds the body. There is a possibility of using acoustical vibrations to control phenomena which occur in the boundary layer. Such phenomena could be directed toward the desired side of a physi- cal body, depending upon the condition of tlie bound- ary layer. DECLASSIFIED NACA REPORTS NACA RM A50J26a AERODYNAMIC CHARACTERISTICS INCLUDING PRESSURE DISTRIBUTIONS OF A FUSELAGE AND THREE COMBINATIONS OF THE FUSELAGE WITH SWEPT-BACK WINGS AT HIGH SUBSONIC SPEEDS. Fred B. Sutton and Andrew Martin. February 6, 1951. 117p. diagrs., photos., tabs. (NACA RM A50J26a) (Declassified from Confidential, 10/14/55} As part of an NACA transonic research program, three sweptback wings with a fuselage were inves- tigated over a Mach number range from 0.40 to 0.94. These model wings had NACA 65A006 sections par- allel to the plane of symmetry. One of the model wings was swept back 35° and had an aspect ratio of 6; the other two were swept back 45° and had aspect ratios of 4 and 6. Force and pitching-moment data, tabulated pressure measurements, downwash and dynamic-pressure characteristics, and tuft studies are presented. The approximate effects of wing elasticity on lift and moment data are also shown. THE FOLLOWING REPORTS HAVE BEEN DECLASSIFIED FROM CONFIDENTIAL 11/14/55, AND ARE UNAVAILABLE: RM L8K18a RM L52K24a THE FOLLOWING REPORTS HAVE BEEN DECLASSIFIED FROM CONFIDENTIAL, 11/14/55 NACA RM A7K28 HIGH-SPEED STABILITY AND CONTROL CHARAC- TERISTICS OF A FIGHTER AIRPLANE MODEL WITH A SWEPT-BACK WING AND TAIL. Charles P. Morrill, Jr., and Lee E. Boddy. April 14, 1948. 47p. diagrs., photos. (NACA RM A7K28) Wind-tunnel tests were made at high subsonic Mach numbers of a model of a pursuit airplane with a 35° sweptback wing and tail. Data are included in the report which show the basic characteristics of the model; the control and hinge-moment characteristics of the horizontal tail, elevator, and aileron; the ef- fect of a wing leading-edge slat; and the effect of a fuselage-side dive brake. UNIVERSITY OF FLORIDA NACA RESEARCH ABSTRACTS NO. 93 NACA RM A9K02 3 1262 08153 293 8 NACA RM A53C19 INVESTIGATION OF DOWNWASH AND WAKE CHARACTERISTICS AT A MACH NUMBER OF 1.53. Ill - SWEPT WINGS. Edward W. Perkins and Thomas N. Canning. February 23, 1950. 41p. diagrs., tab. (NACA RM A9K02) The results of an experimental investigation of the downwash and wake characteristics behind two highly swept wings in a supersonic stream are pre- sented. The leading-edge sweep angles of the two wings were 63° and 63°45', the aspect ratios were 3.50 and 1.66, and the corresponding taper ratios were 0.25 and 1.00. The tests were made at a Mach number of 1.53 and Reynolds numbers of 1.4 million and 2.6 million, respectively. A comparison be- tween experimental and theoretical values of the rate of change of downwash angle with angle of attack at zero lift is made. NACA RM A52K12 TECHNIQUES FOR DETERMINING THRUST IN FLIGHT FOR AIRPLANES EQUIPPED WITH AFTERBURNERS. L. Stewart Rolls, C. Dewey Havill, and George R. Holden. January 1953. 27p. diagrs., photos. (NACA RM A52K12) An experimental technique has been developed which enables a determination of the net thrust for an afterburner -equipped airplane in flight. Measure- ments from a swinging pitot-static pressure and total temperature probe are used to determine the gross thrust, total air-flow rate, and net thrust. Details are also presented for an air-cooled fixed- pressure probe for the determination of basic engine thrust. NACA RM A52K13 TESTS IN THE AMES 40- BY 80 -FOOT WIND TUN- NEL OF AN AIRPLANE MODEL WITH AN ASPECT RATIO 4 TRIANGULAR WING AND AN ALL- MOVABLE HORIZONTAL TAIL - HIGH-LIFT DE- VICES AND LATERAL CONTROLS. Ralph W. Franks. February 1953. 45p. diagrs., photo., 2 tabs. (NACA RM A52K13) Tests have been made of a model consisting of a tri- angular wing in combination with a fuselage of fine- ness ratio 12.5; a thin, triangular, vertical tail with a constant -chord rudder; and a thin, unswept, all- movable horizontal tail. The wing had an NACA 0005 modified section and was equipped with slotted inboard and plain outboard flaps. Tests were made with the wing -fuselage -vertical -tail configuration in addition to the tests of the complete model. The results of tests of lateral and directional controls, the inboard flaps as a high-lift device, and the out- board flaps as a high-lift device are presented. The Reynolds number, based on the wing mean aerody- namic chord, was appro.ximately 10.9 million and the Mach number was about 0.13. EXPERIMENTAL INVESTIGATION OF THE EF- FECTS OF PLAN-FORM TAPER ON THE AERO- DYNAMIC CHARACTERISTICS OF SYMMETRICAL UNSWEPT WINGS OF VARYING ASPECT RATIO. Edwin C. Allen. May 1953. 53p. diagrs., photos., tab. (NACA RM A53C19) This r.eport presents results of tests of a series of symmetrical, unswept, 8-percent-thick wings of varying aspect ratio and taper ratio.' The wings were tested in combination with four different bodies of revolution over a Mach number range from 0.40 to 0.94 with a corresponding Reynolds number range from 2.58 million to 5.90 million. The lift, drag, and pitching-moment data are presented for wings of aspect ratios 2, 3, and 4 and for taper ratios of 0.20 to 1.00. NACA RM E51K15 COMPARISON OF LOCKED-ROTOR AND WIND- MILLING DRAG CHARACTERISTICS OF AN AXIAL- FLOW-COMPRESSOR TYPE TURBOJET ENGINE. K. R. Vincent, S. C. Huntley, and H. D. Wilsted. January 1952. lOp. diagrs. (NACA RM E51K15) The internal drag of an axial -flow turbojet engine with the rotor locked in place to prevent windmilling and with the engine windmilling was obtained over a range of simulated Mach numbers. The corrected internal drag of the engine with the locked rotor was 210 pounds or only 46 percent of the windmilling drag at a flight Mach number of 0.8. NACA RM E53K06 ANALYTICAL STUDY OF LOSSES AT OFF-DESIGN CONDITIONS FOR A FIXED-GEOMETRY TURBINE. Warner L. Stewart and David G. Evans. February 1954. 48p. diagrs., tab. (NACA RM E53K06) An analytical investigation was made to determine the off-design loss characteristics of a fixed- geometry turbine of which the experimental per- formance was known. The method of analysis utilized an effective loss parameter and assumed that the velocity normal to the blade entrance angle was lost as a total -pressure loss. The method also assumed constant tangential component of velocity between the station just upstream and just down- stream of the stator and rotor trailing edge. Good correlation between the analytically and experi- mentally obtained performance was found over the entire map until limiting loading was approached. The large decrease in efficiency at low-speed high pressure ratios and at high-speed low pressure ratios was found in the analysis to be almost en- tirely due to the rotor incidence and turbine exit whirl losses. From the results of the investigation it was concluded that for turbines designed to oper- ate efficiently at more than one point, the design must compromise rotor incidence angle and exit whirl losses. NACA RESEARCH ABSTRACTS NO. 93 NACA RM L8K12a HINGE -MOMENT MEASUREMENTS OF A WING WITH LEADING-EDGE AND TRAILING-EDGE FLAPS AT A MACH NUMBER OF 1. 93. William B. Boatright and Robert W. Rainey. January 14, 1949. 12p. diagrs., tab. (NACA RM L8K12a) Hlnge-monnent data for a wing with leading-edge and tr'ailing-edge flaps of wedge section were obtained in the Langley 9 -inch supersonic tunnel at a Mach num- ber of 1.93 and a Reynolds number of 1.31 x 10^. Curves of hinge moment against angle of attack and against flap deflection are shown, and the results are compared with theory. The possibility of a linkage system to reduce control forces is discussed. NACA RM L8K17a CONTROL EFFECTIVENESS AND HINGE -MOMENT MEASUREMENTS AT A MACH NUMBER OF 1.9 OF A NOSE FLAP AND TRAILING-EDGE FLAP ON A HIGHLY TAPERED LOW-ASPECT-RATIO WING. D. William Conner and Meade H. Mitchell, Jr. January 10, 1949. 26p. diagrs., photo. (NACA RM L8K17a) Nose flaps and trailing-edge flaps were tested on a low-aspect-ratio, highly tapered, half-span wing model in the Langley 9- by 12-inch supersonic blow- down tunnel at a Mach number of 1.9 and a Reynolds number of 3,000,000. Lift, drag, pitching- and rolling-moment data for the wing and hinge-moment data for the flaps were obtained. All tests were made in the presence of a fuselage. NACA RM L8K24a EXPERIMENTAL AND CALCULATED HINGE MOMENTS OF TWO AILERONS ON A 42.7° SWEPT- BACK WING AT A MACH NUMBER OF 1.9. James C. Sivells and Kennith L. Goin. January 19, 1949. 23p. diagrs., photos., tabs. (NACA RM L8K24a) A 42.7° sweptback wing was tested with two types of ailerons in the Langley 9- by 12-inch supersonic blowdown tunnel at a Mach number of 1.9 and a Reynolds number of 2.2 x 10^, The wing had an as- pect ratio of 4, a taper ratio of 0.5 , and an 8- percent-thick biconvex airfoil section. The contour of one aileron was formed by the basic airfoil con- tour, and the other aileron had flat sides and a trailing-edge thickness of one-half the hinge-line thickness. NACA RM L9K01a ROCKET-POWERED FLIGHT TEST OF A ROLL- STABILIZED SUPERSONIC MISSILE CONFIGURA- TION. Robert A. Gardiner and Jacob Zarovsky. January 12, 1950. 32p. diagrs., photos., tab. (NACARM L9K01a) A missile research model incorporafing wing-tip ailerons and a gyro-actuated automatic roll control was flight tested at supersonic speed. The aerody- namic rolling derivatives for zero-lift flight were determined from the flight record. It was concluded that the method used in the preflight system analysis is valid and that the gyro-actuateci4«r=attefQn control system provided a satisfactorv--l»«^a^J roll stabilization in zero-lift^s^ip^l^istJnicTTrghit'/^^^^ NACA RM L9K09 AERODYNAMIC INVESTIGATI^JOF A PARABOLIC BODY OF REVOLUTION AT MAErff*mMBEI? OF 1.92 AND SOME EFFECTS OF AN ANNULAR JET EXHAUSTING FROM THE BASE. Eugene S. Love. February 8, 1950. 75p. diagrs., photos., tab. (NACA RM L9K09) An aerodynamic investigation of a slender pointed parabolic body of revolution was conducted at a Mach number of 1.92 with and without the effects of an annular supersonic jet exhausting from the base. Measurements without the jet in operation were made of lift, drag, pitching moment, base pres- sures, and radial and axial pressures. With the jet in operation, pressure measurements were made over the rear of the body with the primary variables being angle of attack, ratio of jet velocity to stream velocity, and ratio of pressure at jet exit to stream pressure. NACA RM L50K06 HORIZONTAL -TAIL EFFECTIVENESS AND DOWN- WASH SURVEYS FOR TWO 47.7° SWEPTBACK WING-FUSELAGE COMBINATIONS WITH ASPECT RATIOS OF 5.1 AND 6.0 AT A REYNOLDS NUMBER OF 6.0 X 10^. Reino J. Salmi. January 12, 1951. 65p. diagrs., photos., 2 tabs. (NACA RM L50K06) Results of wind-tunnel tests on two 47.7° sweptback wing-fuselage combinations of aspect ratios 5.1 and 6.0 to determine the effects of the vertical location of a horizontal sweptback tail on tail effectiveness and the static longitudinal stability were presented. The tests were made at a Reynolds number of about 6.0 X 10^ (Mach number of 0.14) for various combi- nations of leading-edge and trailing-edge flaps. The results of airstream surveys in the region of the tail are also presented. 10 NACA RM L50K29 LOW-SPEED LONGITUDINAL AND WAKE AIR- FLOW CHARACTERISTICS AT A REYNOLDS NUM- BER OF 6.0 X 106 OF A 52° SWEPTBACK WING EQUIPPED WITH VARIOUS SPANS OF LEADING- EDGE AND TRAILING-EDGE FLAPS, A FUSELAGE, AND A HORIZONTAL TAIL AT VAWOUS VERTICAL POSITIONS. Roland F. Griner and Gerald V. Foster. February 28, 1951. 66p. diagrs., photo., 3 tabs. (NACA RM L50K29) The results are presented of an investigation con- ducted in the Langley 19-ioot pressure tunnel at a Reynolds number of 6.0 x 10^ to determine the ef- fects of leading-edge-flap spans on an NACA 64- series wing swept back 52°. Several of the more satisfactory spans of leading-edge flaps were inves- tigated with various combinations of trailing-edge flaps, fences, a fuselage, and a horizontal tail. Sur- veys of downwash angle, sidewash angle, and dy- namic pressure ratio behind the wing at approxi- mately the location of a horizontal tail are presented. NACA RM L51I05 EFFECT OF FORMATION POSITION ON LOAD FACTORS OBTAINED ON F2H AIRPLANES. Carl R. Huss and Harold A. Hamer. December 1951. 15p. diagrs., 3 tabs. (NACA RM L51I05) Plots of load factor against airplane position are presented for three combinations of four airplanes hying in formation. The plots show that the load- factor trend was to increase toward the end of the formation. Typical time histories are presented. NACA RML51K30 TIME HISTORIES OF MANEUVERS PERFORMED WITH AN F-86A AIRPLANE DURING SQUADRON OPERATIONS. Harold A. Hamer and Campbell Henderson. February 1952. 90p. diagrs., 3 tabs. (NACA RM L51K30) Some preliminary results of maneuvers performed during U. S, Air Force squadron operations with an F-86A jet-fighter airplane are presented in time- history form. The maneuvers cover a speed range from the stall to 530-mile-per-hour indicated air- speed and pressure altitudes varying from sea level to approximately 25.000 feet. Variation of the maximum airplane linear and angular accelerations experienced during the investigation are also pre- sented. NACA RESEARCH ABSTRACTS NO. 93 NACA RM L52K07 FREE -FLIGHT INVESTIGATION AT ZERO UFT IN THE MACH NUMBER RANGE BETWEEN 0.7 AND 1.4 TO DETERMINE THE EFFECTIVENESS OF AN INSET TAB AS A MEANS OF AERODYNAMICALLY RELIEVING AILERON HINGE MOMENTS. William M. Bland, Jr., and Edward T. Marley. January 1953. 19p. diagrs., photos. (NACA RM L52K07) An experimental investigation employing a technique which utilized a zero-lift rocket -propelled model in free flight has been made to determine some of the characteristics of an inset tab as an aerodynamic balance in the Mach number range between 0.7 and 1.4. The fixed, 0.09-chord, full-span, inset tab that was investigated was attached to a 0.3-chord full-span aileron on a wing of aspect ratio 3 and taper ratio 0.6 that had the quarter-chord line swept back 45° and NACA 65A006 airfoU sections parallel to the model center line. Results of this investiga- tion show that the tab was capable of balancing (trim- ming) the aileron hinge moments throughout the Mach number range investigated even though the effective- ness of the tab decreased with increasing Mach num- ber. It was shown that the aileron rolling effective- ness was decreased considerably when the tab was used to reduce the aileron hinge moments. The tab when considered as a servotab was an effective aero- dynamic balance for Mach numbers less than 1.1. At no time during the investigation did the mass- balanced aileron show any evidence of buzz or flutter. It was also shown that the tab effectiveness could be estimated with reasonable accuracy from e^qjerimen- tal data and from thin-airfoil theory. NACA RM L52K25 INVESTIGATION OF THE EFFECT OF CHORDWISE POSITIONING AND SHAPE OF AN UNDERWING NA- CELLE ON THE HIGH-SPEED AERODYNAMIC CHARACTERISTICS OF A 45° SWEPTBACK TAPERED-IN-THICKNESS-RATIO WING OF AS- PECT RATIO 6. H. Norman Silvers and Thomas J. King, Jr. January 1953. 50p. diagrs. (NACA RM L52K25) An investigation at high ^eeds of chordwise posi- tioning of underwing nacelles at a spanwise location of 0.46 semispan with an ogive -cylinder shape (fineness ratio = 9.34), an NACA 65A-series airfoil of revolution shape (fineness ratio = 10.68), and a modified NACA 0-series airfoil of revolution shape reversed in direction (fineness ratio = 10.04) was made on a small-size 45° sweptback tapered-in- thickness-ratio wing of aspect ratio 6. NACA RESEARCH ABSTRACTS NO. 93 NACA RM L53K16 AN AIR-FLOW-DIRECTION PICKUP SUITABLE FOR TELEMETERING USE ON PILOTLESS AIRCRAFT. Wallace L. Ikard. March 1954. 25p. diagrs., photos. (NACA RM L53K16) A vane-type air-flow-direction pickup is described which is suitable for telemetering angle-of-attack and angle-of-sideslip data from rocket-propelled pilotless aircraft models. Test results which are presented show that the device performs well under high accelerations and is stable throughout a Mach number range from subsonic to above a Mach num- ber of 2.5. NACA RM L53K18 EXPERIMENTAL INVESTIGATION OF THE OSCIL- LATING FORCES AND MOMENTS ON A TWO- DIMENSIONAL WING EQUIPPED WITH AN OSCIL- LATING CIRCULAR-ARC SPOILER. Sherman A. Clevenson and John E. Tomassoni. January 1954. 20p. diagrs., photos. {NACA RM L53K18) Results of a wind-tunnel investigation of the forces, moments, and phase angles on a two-dimensional wing equipped with an oscillating circular -arc spoiler are presented. Schlieren photographs are presented which show the flow over and behind the spoiler. Data for Reynolds numbers from 1.3 x 10° to 6.3 X 10^, Mach numbers from 0.2 to 0.82, and reduced frequencies from to 0.92 on the normal- force and pitching-moment coefficients and their respective phase angles referred to spoiler position are indicated. NACA RM L53K30 PRELIMINARY INVESTIGATION OF THE FLOW IN AN ANNULAR-DIFFUSER— TAILPIPE COMBINA- TION WITH AN ABRUPT AREA EXPANSION AND SUCTION, INJECTION, AND VORTEX-GENERATOR FLOW CONTROLS. John R. Henry and Stafford W. Wilbur. February 1954. 27p. diagrs. (NACA RM L53K30) The performance of an annular-diffuser — tailpipe combination with an abrupt area expansion was in- vestigated with and without flow controls in the form of suction, injection, and vortex generators. The diffuser had a 21 -inch-diameter straight outer wall, an area ratio of 1.9 to 1, and fully developed pipe flow at the inlet. Inlet Mach number was varied be- tween 0.18 and 0.43. The ratio of the auxiliary air flow to the flow of the main stream was varied from to approximately 4 percent. (Both suction and injection flow controls were effective in producing improved diffuser performance. ) NACA - Langley Field. Vj.


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Diabetes reversal after bypass surgery linked to changes in gut microorganisms
Friday, July 8, 2016
Weight loss from bariatric surgery appears to reverse premature aging
Thursday, July 7, 2016
Missing link in epigenetics could explain conundrum of disease inheritance
Wednesday, July 6, 2016
How obesity contributes to, blocks treatment of pancreatic cancer
Your kids are what you eat, researchers show
'Hunger' neurons in the brain are regulated by protein activated during fasting
Global obesity estimates may miss more than half a billion worldwide
Obese preschoolers have 60 percent higher healthcare costs than healthy weight children
Moderate and vigorous exercise have comparable effects on nonalcoholic fatty liver disease
Tuesday, July 5, 2016
Policymakers fall short on global agreement to reduce marketing unhealthy foods to kids
Higher consumption of unsaturated fats linked with lower mortality rates
More calories consumed from subsidized food commodities linked to cardiometabolic risks
Extra fat does not act as an insulator
Link between stress hormone, obesity in depressed, bipolar patients
Monday, July 4, 2016
How lifestyle intervention for weight loss affects birth rates in women with a high BMI
Pasta is not fattening -- quite the opposite, Italian study finds
Friday, July 1, 2016
Cravings for high-calorie foods may be switched off in the brain by new supplement
Thursday, June 30, 2016
Resistant starch may benefit people with metabolic syndrome
Researchers identify calorie-burning pathway in fat cells
Study finds potential treatment for non-alcoholic fatty liver disease
Weight-loss technologies train the brain to resist temptation
Wednesday, June 29, 2016
How a low-calorie diet could extend lifespan
Educating parents on healthy infant sleep habits may help prevent obesity
Modeling NAFLD with human pluripotent stem cell derived immature hepatocyte like cells
Overweight youths at greater risk for heart failure
Tuesday, June 28, 2016
Childhood binge eating: Families, feeding, and feelings
Obesity linked to increased risk of multiple sclerosis
Fish oil during pregnancy offers no protection for children against obesity
Study uses diverse sample to examine childhood weight's link to age of first substance use
Monday, June 27, 2016
Overweight or not, mannose levels may indicate diabetes risk
Friday, June 24, 2016
Parents, especially fathers, play key role in young adults' health
In mice, daughters of overweight dads have altered breast tissue, higher cancer risk
Thursday, June 23, 2016
Overweight and obesity impact on periodontitis
Wednesday, June 22, 2016
For women, healthy diets may help with mobility when aging
Is 'when we eat' as important as 'what we eat'?
Tuesday, June 21, 2016
Overweight, obese type 2 patients show improvements with structured nutrition therapy
Improvement seen in US diet
New link found between diabetes, Alzheimer's disease
Insulin-sensitive fat leads to obesity
Monday, June 20, 2016
Scientists discover on/off switch for obesity-associated cancer
Thursday, June 16, 2016
Your weight as a teenager is linked to your risk of heart failure in early middle age
Pregnant women's high-fat, high-sugar diets may affect future generations
How fat becomes lethal, even without weight gain
Overweight adolescent men more likely to develop severe liver disease later in life
A single species of gut bacteria can reverse autism-related social behavior in mice
Wednesday, June 15, 2016
Broken calorie sensing pathway: How overeating may lead to more eating
The Muffin Study: Mono- vs. polyunsaturated fats in patients with metabolic syndrome
Age, obesity, dopamine appear to influence preference for sweet foods
Tuesday, June 14, 2016
Bariatric surgery significantly improves lipid profile in obese patients
Consistent links between capacity to delay gratification, ADHD, obesity
Healthy plant-based diet linked with substantially lower type 2 diabetes risk
Specific enzyme linked to process of metabolic dysfunction in aging
New insights uncovered into Prader-Willi syndrome
Study compares effectiveness of weight-loss drugs
Revised UK 'Eatwell Guide' promotes industry wealth not public health, argues expert
Monday, June 13, 2016
Breastfeeding, antibiotics before weaning and BMI in later childhood
Proper maternal folate level may reduce child obesity risk
Friday, June 10, 2016
New tool brings personalized medicine closer
Thursday, June 9, 2016
New insights into mechanism of metabolic disorders: Proteome of an entire family
Obesity and smoking reduces likelihood of treatment success in early rheumatoid arthritis
Wednesday, June 8, 2016
Late sleep timing linked to poorer diet quality, lower physical activity
How altered gut microbes cause obesity
Tuesday, June 7, 2016
Fat tissue shows a robust circadian rhythm in a dish
Findings suggest small increase in obesity among U.S. teens in recent years
Prevalence of obesity in U.S. increases among women, but not men
Mediterranean diet high in healthy fat does not lead to weight gain, according to randomized trial
Some Asian-Americans are predisposed to want more carbs, fast food
What happens when parents comment their daughter's weight?
New approach to MRI imaging links saturated fats to breast cancer in postmenopausal women
Monday, June 6, 2016
Copper is key in burning fat
Just a few more bites: Defining moderation varies by individual, study finds
Obesity, gestational diabetes in mothers linked to early onset of puberty in daughters
Family-based weight management program improved self-perception among obese children
Intervention reduces rates of overweight tots by half
Lean gene discovery could lead to new type 2 diabetes therapies
Epigenomic alterations contribute to obesity-associated diabetes
Increase in obesity among pediatric Hodgkin Lymphoma patients may be linked to disease relapse
Saturday, June 4, 2016
Obesity continues to increase in Sweden, even in the last few years
Overweight very young children consume larger meals
Thursday, June 2, 2016
Mortality is much lower in obese patients who have obesity surgery compared with those who don't
Current apps on weight management have not been certified by health authorities and there are no published data on their effectiveness
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subset: commoncrawl


text:
$4995Buy Now
Ideas for useThe possibilities are endless but here are a few ideas for using this name:
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A straightforward name built to convey expertise in financial and insurance-related affairs. It carries a headstrong no-nonsense sound that makes it highly professional.
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They have the best deals around!!!
Jonesboro Freds
1. Fred's Super Dollar
4212 E Johnson AveJonesboro, AR 72401
From Business: Founded in 1947, Fred's Inc. operates as mass merchant and a discount dollar/drug store. Located in Jonesboro, Ark., it has approximately 669 discount general merch…
2. Fred Meyer Jewelers
1525 S Caraway RdJonesboro, AR 72401
3. Fred Meyer Jewelers
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4. Fred's Super Dollar
2308 S Caraway RdJonesboro, AR 72401
From Business: Founded in 1947, Fred's Inc. is a combination of discount dollar store, drug store and mass merchant. It offers a wide range of products under categories, including…
5. Fred Dacus Associates Realtors
2529 S Caraway RdJonesboro, AR 72401
From Business: * Jonesboro's Leading Real Estate Company * Voted Best Real Estate Co. and Best Sales Team by Jonesboro Sun Readers * Number One in Sales in Jonesboro MLS in 2002 *…
6. Hargett, Fred Marvin
611 E Washington AveJonesboro, AR 72401
7. Fred and Shelby's Express Mart
500 S Gee StJonesboro, AR 72401
8. Huggins, Fred J, MD
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9. Angulo Alfred F Jr
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10. Fred Bennett
3190 Highway 228Walnut Ridge, AR 72476
11. Fred's Super Dollar
1723 W KingshighwayParagould, AR 72450
12. Holland Alfred J
609 S 7th StParagould, AR 72450
13. Fred's Super Dollar
1301 N Illinois StHarrisburg, AR 72432
From Business: Fred's Inc. has been operational since 1947, operating discount general merchandise stores. Based in Harrisburg, Ark., the company operates more than 700 stores, in…
14. Fred's Pharmacy
1301 S Illinois StHarrisburg, AR 72432
From Business: Established in 1947, Fred's Inc. operates as mass merchant and a discount dollar/drug store. Based in Harrisburg, Ark., it operates nearly 700 discount general merc…
15. Fred's Super Dollar
800 S State Highway 77Manila, AR 72442
16. Fred's Super Dollar
801 N State Highway 77Manila, AR 72442
17. Fred's Super Dollar
103 Dawson StMarked Tree, AR 72365
18. Lewis Fred C - CLOSED
3009 Woodsprings RdJonesboro, AR 72404
19. Lewis Fred Tent Rentals - CLOSED
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20. Walmart Neighborhood Market
2600 Linwood DrParagould, AR 72450
From Business: Visit your newest Walmart today. Walmart always features a great selection of high-quality merchandise, friendly service &, of course, Every Day Low Prices. From fr…
21. J C Penny StoreServices
3000 E Highland DrJonesboro, AR 72401
22. Dollar General
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23. Deals Nothing Over A Dollar - CLOSED
1211 S Caraway RdJonesboro, AR 72401
24. Kmart
I like things I find at Kmart that you don't find other places... It's like a wal-mart... yet different. Some different toys ... and ... other thin…
25. T.J. Maxx
I have been to great tj maxx stores but this one has absolutely no selection. Not recommended.
26. Deal$
6624 Stadium BlvdJonesboro, AR 72404
27. Surplus Warehouse
385 E Johnson AveJonesboro, AR 72401
28. Family Dollar
316 E Johnson AveJonesboro, AR 72401
29. Save-A-Lot
Its a good working envorment i've me wit save-A-Lot for 7 years As long as you show up on time do your job and, dont miss no days unless emerg. You …
30. Big Lots
1907 Woodsprings RdJonesboro, AR 72401


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Sheraton Shanghai Hongkou Hotel provides more than 1,200 square meters of event space with 12 distinctive event rooms, which can be transformed into truly unique settings for every occasion. With crystal chandeliers hanging from a 6.5-meter ceiling, our Grand Ballroom spans 600 square meters and can accommodate up to 680 guests. Meanwhile, the new 300-square-meter Crystal Ballroom can host up to 340 people.
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Top Definition
A short way to say breakfast; slang for the first meal of the day.
A little brecky could be good.
dodane przez styng88 styczeń 07, 2007
Trending Now
A morning meal usually prepared while on vacation by an individual with no culinary experience. Aside from the food prepared the chef wanna-be must prepare a blended alcoholic beverage and must be drinking while cooking.
How does french toast, bacon, sausage, and some rum runners sound for breckies tomorrow?
dodane przez Dubble J listopad 14, 2011


text:
no more black hole comms in story EC?
View Single Post
There are less and less reasons to run old content, and for my new 50 characters more and more irritations on gearing up.
I think it is poor judgement to retro nerf things that should have been setup this way in the first place. I understand that SM's can now be ran in columi, and get rakata. That makes them truly tier 1, and that is great.
However SM Denova and SM TFB are not possible to run in columi, and only drop rakata except 2 BH pieces, one from each of the last bosses. So basically you have to be in Rakata Plus to run these, but there is no point to continually run them when you have 8 people with 12 needed bh items and only 2 items drop per run. Yes you can still do your dailies for comms, but the fact that you have nerfed the ability to get a full BH geared toon out to being MONTHS instead of weeks is detrimental to the community.
No bh in Tier 1? EV/KP? ABSOLUTELY
But once you get to SM EC you are now on par with the hard mode tier 1's, and already have full rakata. What is the point in running them?
Established 50's this isnt going to affect too much, but alts and NEW PLAYERS will be alienated by this change. And you people need MORE new players, not less.
Yoshua Acero
Pre-Cu Bria Vet - Master Doc/Master swords
Paid 15$ at Gamestop for my CE!


text:
Will a MySQL database hold over 103,998,960,000 records or will have to spread this out between several databases?
We started with Q&A. Technical documentation is next, and we need your help.
Whether you're a beginner or an experienced developer, you can contribute.
closed as not a real question by Lion, CloudyMarble, Dipesh Parmar, EJP, zessx Mar 1 '13 at 10:29
It's difficult to tell what is being asked here. This question is ambiguous, vague, incomplete, overly broad, or rhetorical and cannot be reasonably answered in its current form. For help clarifying this question so that it can be reopened, visit the help center.If this question can be reworded to fit the rules in the help center, please edit the question.
It depends a little bit on the size of a record. There is no limit ot the number of rows, but there is a 64 terrabyte limit on the size of data.
If you are within that limit and you make sure your primary key does not overflow (which it wont in your case assuming a uint primary key) then you will be fine.
If table size not matter you can use a very big count of rows. From mysql documentation.
For more information MySQL Source configuration.
Edit: From comments i get i should give information about engine wise.
For more information about MyISAM engine limit.
For more information about InnoDB engine limit.
Theoretically yes but in real life there are limitations like Table size and insert time. From MySQL documentation again.


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Simon Sebbag
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text:
2002 Chevrolet Camaro for Sale in Edmonton, Alberta
2002 Chevrolet Camaro
Z28 Convertible 6-Speed Manual
- Stock #: C0004
- Trim: Z28 Convertible 6-Speed Manual
- Exterior Colour: Orange
- Interior Colour: Black
- Number of Doors: 2
- Engine: 5.7L V 8
- Transmission: 6 Spd Manual
- Drive Type: RWD
- Upholstery: leather
- Odometer: 71,341 Kms
This very well cared for 2002 Camaro has had the same owner for the last 10 years. Always kept indoors though winter this car shows the pride of ownership and care given over the years. The 2002 Camaro was the final year of production and less they 5% of all Camaro's in this year where this very limited Sunset Orange metallic color. If you are looking for an investment or just a very nice summer driver this car could be for you. Priced at under 20000 dollars this is a lot of 8V top down fun for not a lot of money. Car includes car cover, convertible top boot, full stereo replacement, and Magaflow exhaust.