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Simulation of crossflow instability on a supersonic highly swept wingA direct numerical simulation (DNS) algorithm has been developed and validated for use in the investigation of crossflow instability on supersonic swept wings, an application of potential relevance to the design of the High-Speed Civil Transport (HSCT). The algorithm is applied to the investigation of stationary crossflow instability on an infinitely long 77-degree swept wing in Mach 3.5 flow. The results of the DNS are compared with the predictions of linear parabolized stability equation (PSE) methodology. In-general, the DNS and PSE results agree closely in terms of modal growth rate, structure, and orientation angle. Although further validation is needed for large-amplitude (nonlinear) disturbances, the close agreement between independently derived methods offers preliminary validation of both DNS and PSE approaches.
Document ID
19960012495
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Pruett, C. David (College of William and Mary Williamsburg, VA, United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1995
Subject Category
Aerodynamics
Report/Patent Number
NIPS-96-08486
NAS 1.26:198267
NASA-CR-198267
Accession Number
96N18732
Funding Number(s)
PROJECT: RTOP 505-59-50-02
CONTRACT_GRANT: F49620-95-1-0146
CONTRACT_GRANT: NAS1-19656
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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