Validation of WIND for a series of inlet flows

Validation assessments compare WIND CFDsimulations to experimental data for a series of inletflows ranging in Mach number from low subsonic tohypersonic. The validation procedures follow theguidelines of the AIAA. The WIND code performswell in matching the available experimental data. Theassessments demonstrate the use of WIND and provideconfidence in its use for the analysis of aircraft inlets. Introduction The NASA Glenn Research Center (GRC) isinvolved in the design and analysis of inlet concepts foraerospace vehicles that operate at Mach numbersspanning the range from low subsonic to hypersonic.Inlet flow fields are fairly complex. The external flowenters the inlet and passes through internal ducting thatmay involve significant turning and curvature to reachthe engine. The curvature of internal ducting promotessecondary flows. The viscous flow on the vehicle andinlet surfaces may consist of laminar boundary layerstransitioning to turbulent boundary layers. The inlet is aflow compression device, and so, the flow exists in anadverse pressure gradient. Supersonic flows usuallycontain shock waves that then interact with theboundary layers. All these features potentially lead toboundary layer separation. At hypersonic Machnumbers, the possibility of high-temperature effectsexists. The flow may consist of local unsteady featuressuch as time-varying shocks, boundary layers, orboundary layer separation regions. There may exist inthe inlet flow control devices such as bleed holes andslots, jets, and vortex generators.An analysis of the flow in an inlet should providequalitative insight into the general flow features, such*