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Generic Hypersonic Inlet Module AnalysisA computational study associated with an internal inlet drag analysis was performed for a generic hypersonic inlet module. The purpose of this study was to determine the feasibility of computing the internal drag force for a generic scramjet engine module using computational methods. The computational study consisted of obtaining two-dimensional (2D) and three-dimensional (3D) computational fluid dynamics (CFD) solutions using the Euler and parabolized Navier-Stokes (PNS) equations. The solution accuracy was assessed by comparisons with experimental pitot pressure data. The CFD analysis indicates that the 3D PNS solutions show the best agreement with experimental pitot pressure data. The internal inlet drag analysis consisted of obtaining drag force predictions based on experimental data and 3D CFD solutions. A comparative assessment of each of the drag prediction methods is made and the sensitivity of CFD drag values to computational procedures is documented. The analysis indicates that the CFD drag predictions are highly sensitive to the computational procedure used.
Document ID
20040120985
Acquisition Source
Langley Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Cockrell, Chares E., Jr. (NASA Langley Research Center Hampton, VA, United States)
Huebner, Lawrence D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2004
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA Paper 91-3209
Meeting Information
Meeting: AIAA 9th Applied Aerodynamics Conference
Location: Baltimore, MD
Country: United States
Start Date: September 24, 1991
End Date: September 26, 1991
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Public Use Permitted.

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