15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference · 2008 · 12 citations · 3 references
EngineeringAerospace EngineeringAerodynamicsComputational Fluid DynamicsFluid DynamicsAerodynamic DesignBoundary Layer FlowBoundary LayersBoundary-layer TheoryComputational AerodynamicsHypersonic AerodynamicsCore Flow RedistributionFlow PatternFlow Pattern AnalysisHypersonic FlowHypersonic Inlet DesignHypersonic InletsInlet DesignMach Number
A streamline-traced inlet based on the flow within the truncated Busemann inlet is designed, which has a total contraction of 7.9 and internal contraction ratio of 2.6. The boundary layer can destroy the designed flow pattern of the internal flows. Boundary layer correction that realized with the finite differential method is applied to restore the core flow to its designed pattern. CFD tools is used to investigated the flow pattern and mass flow weighted performance of the corrected inlet on its design point of Mach 5.8. Results show the reliability of the correction method and the good performance of the inlet. Copyright © 2008 by the American Institute of Aeronautics and Astronautics, Inc.
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