Application of the Thin-Wing-Expansion Method to the Flow of a Compressible Fluid past a Symmetrical Circular Arc Aerofoil

抄録

Imai’s thin-wing-expansion method is presented in somewhat modified and extended form. Then the method is applied to the flow of a compressible fluid past a symmetrical circular are aerofoil. Analytical expressions for the velocity potential and the velocity distribution over its surface are obtained. For the profile of thickness ratio t=0.1, numerical computations have been carried out at M=0.7 and 0.8. The present method has been proved very useful, because its procedures are simple and clear, and because its convergency and accuracy are very good up to considerably high Mach numbers. Comparisons with the theoretical results for related profiles as well as experimental data have been made.