Diffuser Performance of Two-Stream Supersonic Wind Tunnels.

摘要

A simple theoretical model is presented that determines the inviscid, steady-state diffuser performance of a tunnel with plane, parallel supersonic streams that come into contact downstream of a splitter plate and form an infinitely thin interface. The model predictions can be useful to the design and operation of two-stream supersonic wind tunnels and of aircraft engines in which mixing is done at supersonic speeds. A typical one-stream supersonic wind tunnel consists of a converging-diverging nozzle with a given sonic throat area, a test section in which uniform conditions are maintained, and a diffuser with a second throat for decelerating the flow and recovering the pressure. Choking criteria for such wind tunnels determine the minimum allowable second throat area for which the upstream conditions is the sonic throat area of the supersonic nozzle. In that case, pressure recovery is complete because the mach number at the second throat is sonic and shock wave losses are eliminated. Keywords: Reprints. (JES)