NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login

Press Enter or click the Search button to begin your search.

Back to Results
Validation of High-Speed Turbulent Boundary Layer and Shock-Boundary Layer Interaction Computations with the OVERFLOW CodeThe capability of the OVERFLOW code to accurately compute high-speed turbulent boundary layers and turbulent shock-boundary layer interactions is being evaluated. Configurations being investigated include a Mach 2.87 flat plate to compare experimental velocity profiles and boundary layer growth, a Mach 6 flat plate to compare experimental surface heat transfer,a direct numerical simulation (DNS) at Mach 2.25 for turbulent quantities, and several Mach 3 compression ramps to compare computations of shock-boundary layer interactions to experimental laser doppler velocimetry (LDV) data and hot-wire data. The present paper describes outlines the study and presents preliminary results for two of the flat plate cases and two small-angle compression corner test cases.
Document ID
20080026342
Acquisition Source
Johnson Space Center
Document Type
Conference Paper
Authors
Oliver, A. B. (Purdue Univ. West Lafayette, IN, United States)
Lillard, R. P. (Purdue Univ. West Lafayette, IN, United States)
Blaisdell, G. A. (Purdue Univ. West Lafayette, IN, United States)
Lyrintizis, A. S. (Purdue Univ. West Lafayette, IN, United States)
Date Acquired
August 24, 2013
Publication Date
January 9, 2006
Subject Category
Aeronautics (General)
Meeting Information
Meeting: 44th AIAA Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 9, 2006
End Date: January 12, 2006
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
CONTRACT_GRANT: NNJ04HI12G
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available