Flow of a Supersonic Gas Jet Emating from a Nozzle Over a Concave Wall

The problem on the flow of a supersonic gas jet over a concave wall of any configuration was solved. A method of calculating the gas flow arising as a result of the interaction of a noncalculated supersonic gas jet with a plane wall or a curvilinear one is proposed. Results of measurements of the pressure at the surface of a curvilinear obstacle, over which a supersonic gas jet propagates, and of calculations of the gasdynamic parameters of the gas in the near-wall region of this jet, are presented. The most characteristic regions of a noncalculated supersonic gas jet propagating over a curvilinear reflecting wall, which are of interest for a number of practical applications of such jets and for the constructions of their physical and mathematical models, were determined. The determining parameters of flows in a supersonic gas jet over a concave wall were defined ,and the conductions of their similarity were formulated with regard for the main geometric characteristics of the jet. It is shown that the difference between supersonic gas jets propagating over a curvilinear wall and a plane wall is the pressure difference at their inner and outer boundaries. With the use of formulas of the oblique shock wave theory, the angles of inclination of a noncalculated supersonic gas jet to a concave wall and its gasdynamic parameters in all the regions of the wall were determined.