Figure 6.1. Primary Control of Airspeed and Altitude  LIFT  COEFFICIENT  CL  POWER  REQUIRED  0  AVAILABLE  HI?  \  FOR LIFT EQUAL  TO WEIGHT,  “=  17.2J$-  gs  a  ANGLE OF ATTACK  FOR A STEADY CLIMB,  t  ROC = 33,000  FPM  POWER REQ ’ D-  POWER EXCESS  \  A  7-  IER AVAILABLE  ‘ HIGH WILL ESTABLISH  PO ’ lh  w...-..  SNCY  ..--  -_...  - -.-.  LEVEL  FLIGHT AT  --  t  VELOCITY, KNOTS  A  351  NAVWEPS OO-80T-80  APPLICATION OF AERODYNAMICS  TO SPECIFIC PROBLEMS OF FLYING 