Methods for calculating the transonic boundary layer separation for V/STOL inlets at high incidence anglesA semi-empirical scheme for the prediction of transonic pressure distribution on the surface of V/STOL inlets at high incidence angles has been developed. The investigation is intended to improve the boundary layer calculation and separation prediction by including the effects of shock wave-boundary layer interaction into the Lewis Inlet Viscous Computer Program. Wind-tunnel results and theoretical pressure calculation for critical cases are used in constructing the transonic pressure distribution. The program, which describes the development of the boundary layer and predicts the possible flow separation, can handle the cases of inlets at high incidence angles where local supersonic region may occur in the flow.
Document ID
19780062628
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Chou, D. C. (Iowa Univ. Iowa City, IA, United States)
Lee, H. C. (Iowa, University Iowa City, Iowa, United States)
Luidens, R. W. (Iowa Univ. Iowa City, IA, United States)
Stockman, N. O. (NASA Lewis Research Center Cleveland, Ohio, United States)