A supersonic wind tunnel is designed for M = 3 at the test section with a throat 0.12m in area. The supply pressure and temperature at thenozzle inlet, where velocity is negligible, are 0.152MN m and 20°C. The preliminary design is to be based on the assumption that the flow is isentropic with 1.4 ? = and is one-dimensional at the throat and test section.
Find the mass flow, the test section area and the fluid properties at the throat and test section.