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Computational results for the effects of external disturbances on transition location of bodies of revolution from subsonic to supersonic speeds and comparisons with experimental dataComputational experiments have been performed for a few configurations in order to investigate the effects of external flow disturbances on the extent of laminar flow and wake drag. Theoretical results have been compared with experimental data for the AEDC cone, for Mach numbers from subsonic to supersonic, and for both free flight and wind tunnel environments. The comparisons have been found to be very satisfactory, thus establishing the utility of the present method for the design and development of laminar flow configurations and for the assessment of wind tunnel data. In addition, results of calculations concerning the effects of unit Reynolds numbers on transition are presented. In addition to the AEDC cone, computations have been performed for an ogive body of revolution at zero angle of attack and supersonic Mach numbers. Results are presented for transition Reynolds number and wake drag for external disturbances corresponding to free air and the test section of the AEDC-VKF tunnel. These results have been found to compare quite well with wind tunnel data for cases when surface suction is applied as well as when suction is absent.
Document ID
19900058467
Document Type
Conference Paper
Authors
Goradia, S. H. (NASA Langley Research Center Hampton, VA, United States)
Bobbitt, P. J. (NASA Langley Research Center Hampton, VA, United States)
Harvey, W. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
September 1, 1989
Subject Category
AERODYNAMICS
Report/Patent Number
SAE PAPER 892381
Funding Number(s)
CONTRACT_GRANT: NAS1-18585
Distribution Limits
Public
Copyright
Other