Normal Shock at Mach 1.3 Normal Shock at Mach 1.3 Figure 1. Mach number contours for inviscid Mach 1.3 flow through a normal shock. Introduction This verification case involves the steady, inviscid, adiabatic Mach 1.3 flow with a normal shock.
Supersonic flow enters the normal shock and subsonic flow exits the shock.
This flow is a classic, fundamental supersonic flow whose analytic solution is exact and can be found in any compressible flow textbook, such as the book by Anderson. The supersonic conditions are presented in Table 1 and represent the reference conditions. The choice of pressure and temperature are arbitrary and do not change the basic character of the flow for perfect gases. 2.0 ft with a diameter of 1.0 ft. An analytic solution for the inviscid, supersonic, steady, adiabatic flow through a normal shock is well known and presented in any compressible flow text book.