Numerical and Experimental Investigation of Airframe-Integrated Inlet for High Velocities

Airframe-integrated, three-dimensional fixed geometry inlets for hypersonic Mach numbers are under consideration. The numerical investigation is conducted using the three-dimensional Euler's code. The program calculates local and integral flowfield performances in duct taking into account displacement thickness along the wetted surface on the condition that the flow is nonseparated and the gas is in thermodynamic equilibrium. Sweep sidewall compression inlets with and without struts and transformed types of three-dimensi onal inlets have been examined. The results of flowfield calculations at the exit section and along the duct as a function of Mach number M are given. Two models of three-dimensi onal inlets with and without struts have been tested at A/0, = 2-6. The results of numerical and experimental investigations are compared. Nomenclature Ac = inlet frontal area AN = inlet passage area normal to axis Ox AT = area of captured stream tube at the inlet throat A T = relative throat area, = A T/A c