Abstract
This article presents the results of numerical calculations on a 19.78% scale forebody/inlet model of the F/A-18 at a Mach number of 0.20, an angle of attack of 60 deg, and a sideslip angle of 10 deg. The main purpose of these calculations is to support an upcoming wind-tunnel test program in the prediction of engine inlet compressor face total pressure recovery and flow distortion. The CFD model includes the inlet and lip, and other aircraft components that are considered to be important to inlet performance, such as the ramp/splitter plate, the diverter and leading-edge extension (LEX) slot, and the deflected leading-edge flap. The CFD show complex flow patterns on the fuselage surfaces below the LEX, on the ramp/splitter plate, inlet lip, and inside the inlet. The CFD tends to underpredict total pressure recovery and overpredict the flow distortion at the inlet compressor face.
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