One of the goals of the high alpha technology program (HATP) is to accurately predict the inlet performance for aircraft operating at extreme attitudes (a = 60 deg, /8 = 10 deg). In this article, the numerical results for three cases are presented. The cases studied are full scale, 19.78% model scale at design mass flow, and model scale at a reduced mass flow. The effects of Reynolds number on the predicted flowfleld is demonstrated with the model and full scale calculations. The inlet mass flow is reduced 25% to investigate the effect mass flow rate has on the flow entering the inlet and on the inlet duct performance. All cases are at 30-deg angle of attack and 0-deg yaw. Surface static pressures along the forebody and under the leading edge extension (LEX) agreed well with the data for all three cases. The predicted inlet recoveries obtained for full scale and model scale Reynolds numbers were very similar. The predicted inlet recoveries were lower than data. This discrepancy may be partly due to poor inlet lip definition and grid resolution. The predicted inlet recovery for the reduced mass flow rate case was significantly higher than the design mass flow case. The reduction of inlet mass flow rate had a small effect on the external flowfleld. The choice of the turbulence model length scale has a significant impact on the position of the windward side LEX vortex.
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