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Supersonic flow computations for an ASTOVL aircraft configuration, phase 2, part 2A unified space/time marching method was used to solve the Euler and Reynolds-averaged Navier-Stokes equations for supersonic flow past an Advanced Short Take-off and Vertical Landing (ASTOVL) aircraft configuration. Lift and drag values obtained from the computations compare well with wind tunnel measurements. The entire calculation procedure is described starting from the geometry to final postprocessing for lift and drag. The intermediate steps include conversion from IGES to the patch specification needed for the CFD code, grid generation, and solution procedure. The calculations demonstrate the capability of the method used to accurately predict design parameters such as lift and drag for very complex aircraft configurations.
Document ID
19900013430
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Ramakrishnan, Sekaripuram V.
(Rockwell International Science Center Thousand Oaks, CA, United States)
Chakravarthy, Sukumar R.
(Rockwell International Science Center Thousand Oaks, CA, United States)
Szema, Kuo-Yen
(Rockwell International Science Center Thousand Oaks, CA, United States)
Date Acquired
September 6, 2013
Publication Date
May 1, 1990
Publication Information
Publisher: NASA
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
NASA-CR-4284
NAS 1.26:4284
Accession Number
90N22746
Funding Number(s)
PROJECT: RTOP 505-60-01-02
CONTRACT_GRANT: NAS1-17492
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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