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Introduction to VSTOL concepts
Theoretical and applied aerodynamics
Aerodynamics of the wing
10 other sections not shown
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aerodynamic aircraft angle of attack approximately aspect ratio assumed Biot-Savart law blade stall boundary layer C,max calculated chord CLmax component configuration Consider constant control surface critical Mach decrease defined deflected dimensionless distribution downwash drag coefficient ducted propeller elliptic wing equal equation experimental extended chord factor finite wing flow fluid forward flight forward speed free-stream velocity function geometry given gross weight ground effect helicopter rotor Hence hover increase increment induced drag induced power induced velocity integral jet flap laminar leading edge lift coefficient lift curve Mach number maximum mean streamline momentum theorem NACA obtained pitch power required predicted presented in Fig produce profile drag profile power radius referred retreating blade stall Reynolds number rotation shown in Fig slipstream slots STOL thickness thrust augmentation thrust coefficient trailing edge trailing vortex sheet two-dimensional V/STOL vane vector velocity induced vertical vortex system vortices VTOL zero