| Abstract: | The interference of supersonic flows on the concave surface of conical wings was experimentally investigated in 1] for various values of the camber and angles of attack. In order to establish the detailed structure of the interference flow the laminar flow past a wing model in the form of half the surface of a circular cone with vertex angle 2 k = 34° was numerically modeled within the framework of the quasiconical approximation for the three-dimensional Navier-Stokes equations 2]. Under this assumption, confirmed by analysis of the experimental data 1], it was found that the displacement of the external inviscid flow as a result of intense flow separation beyond the leading edges leads to flow patterns similar to those realized on V wing's with a break in the transverse contour 3]. At nonzero angles of attack weak secondary separation was detected beneath the flattened regions of primary separation located in the shaded parts of the concave surface.Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 4, pp. 130–136, July–August, 1989. |
