National Aeronautics and Space Administration

14. Sponsoring Agency Code A number of control-volume models used to analyze the shock- boundary-layer-bleed inter-action were investigated. The bleed assumptions of the various models and their influence on the analytical solutions a r e discussed. The results of the analysis using these models are compared with experimental boundary-layer data taken in a supersonic inlet. The experi-mental Mach number upstream of the interaction was 1. 6 6, and the oblique-shock p res su re rat io was 1. 3 3. The boundary-layer data included bleed flow ra t e s up to approximately 0. 6 of the upstream boundary-layer mass flow rate. Two models proved significantly better when compared with the experimental data. The first model assumed the bleed was removed f rom the control volume with a momentum that was characterized by a p res su re intermediate be-tween the upstream and downstream p res su res. ume was bounded by a streamline dividing the bleed and residual flows. This model elim-inated the need to specify the momentum of the bleed flow. Comparison of the results using the two models showed that specifying the bleed pressure in one model was equivalent to specifying the p re s su re along the dividing streamline in the other. The second model assumed the control vol-Security Classif. (of this page