Present paper gives the experimental results of the aerodynamic interaction phenomena between a secondary air jet and a primary supersonic flow of Mach numbers 2 and 3. The models used are flat plates with a sharp leading edge having a slit at some distance from the leading edge. The secondary jet is injected perpendicularly to the main flow at sonic jet velocity. The parameters varied are the main and the secondary flow conditions as well as the distance from the leading edge to the slit. It is observed that appreciable change in pressure distribution appears only in the upstream part of the slit due to the change of the distance from the leading edge to the slit. It becomes clear that integrated quantities such as force, moment and centre of pressure on the flat plate in various cases of experiment are well arranged by using the ratio of the secondary to the main flow momentum, and that their depending on the downstream part of the slit is not small compared to that on the upstream.
超音速における側方二次噴射に関する実験的研究
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