Abstract
An analysis is presented for calculating the steady three-dimensional flow field in supersonic mixedcompression inlets at incidence. A zonal modeling approach is employed to obtain the solution. The supersonic core flow is computed using a second-order pentahedral bicharacteristic algorithm. The bow shock wave and the reflected internal shock train are determined using a three-dimensio nal discrete shock-fitting procedure. The boundary-layer flow adjacent to both the centerbody and the cowl is computed using a second-order implicit finite difference method. The flow in a shock-wave/boundary-layer interaction region is computed using an integral formulation. The culmination of this research effort is the development of a production-type computer program capable of analyzing the flow in a variety of mixed-compres sion aircraft inlets. Numerical results and correlations with experiment are presented to illustrate application of the analysis.
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