Analytical Computation of Leading-Edge Truncation Effects on Inviscid Busemann-Inlet Performance

An approach is presented to analytically predict the conservation-averaged, inviscid Busemann inlet performance properties at the throat, accounting for the effect of leading edge truncation. A control volume is drawn such that the calculation of throat inlet performance relies on the accurate prediction of the pressure integral along the surface. The pressure integral is predicted by assuming a leading edge total pressure loss and a Mach number distribution similar to a non-truncated Busemann inlet. The resulting surface profiles can also be used to predict the bow and terminating shock wave shapes. The pressure integral prediction approach is compared with a set of inviscid, axisymmetric CFD solutions on the same geometries. The comparisons show that the pressure integral prediction approach compares favorably with the CFD solutions for inlets with moderate contraction ratio and truncation angles no greater than 5°.