International Journal of Aerospace Engineering / 2017 / Article / Tab 1

Research Article

Experimental Study on Aerodynamic Heating Induced by Dual Injections into Hypersonic Cross Flow

Table 1

Test flow parameters.

Mach number, Total pressure, Static pressure, Total temperature, Re

8.14.0 [MPa]377 [Pa]876 [K]6.5 × 106 [m−1]