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Design and Analysis Tool for External-Compression Supersonic InletsA computational tool named SUPIN has been developed to design and analyze external-compression supersonic inlets for aircraft at cruise speeds from Mach 1.6 to 2.0. The inlet types available include the axisymmetric outward-turning, two-dimensional single-duct, two-dimensional bifurcated-duct, and streamline-traced Busemann inlets. The aerodynamic performance is characterized by the flow rates, total pressure recovery, and drag. The inlet flowfield is divided into parts to provide a framework for the geometry and aerodynamic modeling and the parts are 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 analysis. SUPIN provides inlet geometry in the form of coordinates and surface grids useable by grid generation methods for higher-fidelity computational fluid dynamics (CFD) analysis. SUPIN is demonstrated through a series of design studies and CFD analyses were performed to verify some of the analysis results.
Document ID
Document Type
Technical Memorandum (TM)
Slater, John W.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 26, 2013
Publication Date
August 1, 2012
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
Meeting Information
50th Aerospace Sciences Meeting(Nashville, TN)
Funding Number(s)
WBS: WBS 984754.
Distribution Limits
Work of the US Gov. Public Use Permitted.
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