Studies of leading-edge thrust phenomena

摘要: A study of practical limitations on achievement theoretical leading-edge thrust has been made and an empirical method for estimation attainable developed. The is based 1) a analysis set two-dimension al airfoils to define dependence airfoil geometric characteristics arbitrarily defined limiting pressures, 2) examination experimental data provide estimate pressure local Mach number Reynolds number, 3) employment simple sweep theory adapt the three-dimensi onal wings. Because takes into account spanwise variation section characteristics, opportunity afforded design by iteration maximize attendant performance benefits. applicability was demonstrated comparisons aerodynamic series wing-body configurations. Generally, good predictions its influence lift drag were obtained over range numbers from 0.24 2.0. b c