Aerodynamics of V/STOL Flight

addition aerodynamic aircraft airfoil angle of attack application approximately aspect ratio assumed becomes blade boundary layer C₁ calculated camber cascade Chapter chord coefficient combination component configuration Consider constant correction curve decrease defined deflected depends determined developed direction disk distribution drag duct edge effect equal equation expressed factor figure flap flight flow follows forces forward function geometry given helicopter Hence hover increase induced integral leading lift limiting loading maximum mean method momentum normal obtained performance pitch plane power required predicted presented pressure problem produce propeller radius ratio referred rotor seen separation shown in Fig slipstream slots speed stall static streamline surface theorem theory thickness thrust trailing V/STOL vary velocity vertical vortex vortex sheet weight wing zero