Print Email Facebook Twitter Laminar separation at hypersonic speeds: Cone cavity flow at M=5.3 with injection effect of incidence Title Laminar separation at hypersonic speeds: Cone cavity flow at M=5.3 with injection effect of incidence Author Ginoux, J.J. Thiry, F. Institution Von Karman Institute for Fluid Dynamics Date 1971-06-01 Abstract A previous experimental study of the favorable effect of mass injection into a hypersonic separated laminar flow on pressure .and heat transfer distributions at reattachment has been extended to include the influence of a small incidence of the model. Measurements were made at M = 5.3 on a circular cone with an annular cavity. into which air was injected at rates up to approximately half the boundary layer mass flow at separation. Incidence was varied by half-degree steps in the range zero to two degrees. The reattachment pressure and heat transfer peaks increased on the windward side with incidence and more mass injection was required to maintain them below a given level. The relative locations of these peaks were inverse at zero and two degrees incidence. To reference this document use: http://resolver.tudelft.nl/uuid:156e2c4d-c43e-43d9-9f95-80d21b429757 Publisher Von Karman Institute for Fluid Dynamics Source VKI Training Center for Experimental Aerodynamics Technical Note 75 Part of collection Aerospace Engineering Reports Document type report Rights (c) 1971 Von Karman Institute for Fluid Dynamics Files