CALCULATION OF THE FLOW FIELD IN SUPERSONIC MIXED-COMPRESSION INLETS Al ANGLE OF ATTACK USING THE THREE-DIMENSIONAL METHOD OF CHARACTERISTICS WITH DISCRETE SHOCK WAVE FITTING

摘要

The calculation of the floW field in supersonic mixed-compression aircraft inlets at angle of at tack is accomplished using the method of characteristics for steady three-dimensional flow in conjunction with a discrete shock wave fitting procedure. The influence of molecular transport can be included in the computation by treating the viscous and thermal diffusion terms in the governing partial differential equations as correction terms in the method of characteristics scheme. The culmination of the present research is the development of a production type computer program which is capable of calculating the flow field in a variety of axisymmetric mixed compression aircraft inlets. The results produced by the present analysis agree well with those produced by the two-dimensional method characteristics when axisymmetric flow fields are computed. For three-dimensional flow fields, the results of the present analysis agree well with ex per mental data except in regions of high viscous interaction and boundary layer removal. The presort analysis docs not compute the boundary layer or account for boundary layer bleed. Submitted is a thesis by doseph Valpak lo Purdue University, West Lafayette, Indiana, in partial fulfillment of the requirement for the degree of Doctor of Philosophy, March 1978.