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Wind Code Application to External Forebody Flowfields with Comparisons to Experimental ResultsThe WIND Code, a general purpose Navier-Stokes solver, has been utilized to obtain supersonic external flowfield Computational Fluid Dynamics (CFD) solutions over an axisymmetric, parabolic forebody with comparisons made to wind tunnel experimental results. Various cases have been investigated at supersonic freestream conditions ranging from Mach 2.0 to 3.5, at 0 deg and 3 deg angles-of-attack, and with either a sharp-nose or blunt-nose forebody configuration. Both a turbulent (Baldwin-Lomax algebraic turbulence model) and a laminar model have been implemented in the CFD. Obtaining the solutions involved utilizing either the parabolized- or full-Navier-Stokes analyses supplied in WIND. Comparisons have been made with static pressure measurements, with boundary-layer rake and flowfield rake pitot pressure measurements, and with temperature sensitive paint experimental results. Using WIND's parabolized Navier-Stokes capability, grid sequencing, and the Baldwin-Lomax algebraic turbulence model allowed for significant reductions in computational time while still providing good agreement with experiment. Given that CFD and experiment compare well, WIND is found to be a good computational platform for solving this type of forebody problem, and the grids developed in conjunction with it will be used in the future to investigate varying freestream conditions not tested experimentally.
Document ID
20010050983
Acquisition Source
Glenn Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Frate, F. C. (DYNACS Engineering Co., Inc. Brook Park, OH United States)
Kim, H. D. (NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
September 7, 2013
Publication Date
May 1, 2001
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:210568
AIAA Paper 2001-0226
NASA/TM-2001-210568
E-12532
Meeting Information
Meeting: 39th Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 8, 2001
End Date: January 11, 2001
Sponsors: American Inst. of Aeronautics and Astronautics
Funding Number(s)
PROJECT: RTOP 708-73-20
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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