Design of supersonic three-dimensional inlets using two-dimensional isentropic compression flow

The design of supersonic three-dimensional inlets using the V-shaped body forming a two-dimensional flow including an initial oblique shock wave and a subsequent isentropic compression wave is considered. Such a flow appears attractive for inlets design due to a possibility of obtaining high compression levels of external flow over the inlet ramp with small losses of the total pressure. Numerical computations of the flows around the designed configurations were carried out in design and off-design regimes using Euler code. The flow structure was identified, the aerodynamic characteristics of the inlets were determined. The investigation covers the range of supersonic speeds corresponding to the freestream Mach numbers M_∞= 1.8−2.5.