An Integral Approach to Lifting Wing Theory at Mach One.

摘要

An approach to lifting wing theory at Mach one is presented that utilizes an integral method similar to the Karman-Pohlusen method in boundary layer theory. As in any integral method the results obtained are approximate in nature. Nonetheless,comparison with experimental data shows good agreement in cases for which experimental data are available. The method can easily be used to determine the lift on wings of finite aspect ratio and also to solve transient lifting problems. The method is demonstrated by solving for the pressure distribution on a lifting airfoil of arbitrary symmetric cross-section,the lift on a wing of rectangular platform,and the transient lift on an airfoil due to a sudden change in angle of attack.