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SUPIN: A Computational Tool for Supersonic Inlet DesignA computational tool named SUPIN is being developed to design and analyze the aerodynamic performance of supersonic inlets. The inlet types available include the axisymmetric pitot, three-dimensional pitot, axisymmetric outward-turning, two-dimensional single-duct, two-dimensional bifurcated-duct, and streamline-traced inlets. The aerodynamic performance is characterized by the flow rates, total pressure recovery, and drag. The inlet flow-field is divided into parts to provide a framework for the geometry and aerodynamic modeling. Each part of the inlet is defined in terms of geometric factors. The low-fidelity aerodynamic analysis and design methods are based on analytic, empirical, and numerical methods which provide for quick design and analysis. SUPIN provides inlet geometry in the form of coordinates, surface angles, and cross-sectional areas. SUPIN can generate inlet surface grids and three-dimensional, structured volume grids for use with higher-fidelity computational fluid dynamics (CFD) analysis. Capabilities highlighted in this paper include the design and analysis of streamline-traced external-compression inlets, modeling of porous bleed, and the design and analysis of mixed-compression inlets. CFD analyses are used to verify the SUPIN results.
Document ID
Document Type
Conference Paper
Slater, John W.
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
August 5, 2016
Publication Date
January 4, 2016
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
Meeting Information
AIAA SciTech 2016(San Diego, CA)
Funding Number(s)
WBS: WBS 110076.
Distribution Limits
Work of the US Gov. Public Use Permitted.
computational fluid dynamics
supersonic inlets
aerodynamic design
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