Figure 3.9. Transonic Flow Patterns (sheet 2 of 2)  WING IN TRANSONIC FLOW  I  M = .700  a= +2O CL= ,370  NO SHOCK WAVES  I  I  M-.800  a=+2O  CL=.442  SHOCK FORMATION IS APPARENT AT  25 TO 30 % CHORD POSITION  I  M=.075  a=+20  CL=.450  SHOCK INDUCED SEPARATION ALONG  AFT PORTION OF WING PLAPJFORM  NAVWEPS OD-801-80  HIGN SPEED AEQODYNAMICJ 