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Subsonic longitudinal and lateral-directional static aerodynamic characteristics of a general research fighter configuration employing a jet sheet vortex generatorA configuration concept for developing vortex lift, which replaces the physical wing strake with a jet sheet generated fluid strake, was investigated on a general research fighter model. The vertical and horizontal location of the jet sheet with respect to the wing leading edge was studied over a momentum coefficient range from 0 to 0.24 in the Langley 7- by 10-foot high speed tunnel over a Mach number range from 0.3 to 0.8. The angle of attack range studied was from -2 to 30 deg at sideslip angles of 0, -5, and 5 deg. Test data are presented without analysis.
Document ID
19780012128
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Huffman, J. K. (NASA Langley Research Center Hampton, VA, United States)
Fox, C. H., Jr. (NASA Langley Research Center Hampton, VA, United States)
Ziegler, H. (Northrup Corp.)
Date Acquired
September 3, 2013
Publication Date
January 1, 1978
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-74049
Accession Number
78N20071
Funding Number(s)
PROJECT: RTOP 505-11-23-13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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