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Vortex flap flow reattachment line and subsonic longitudinal aerodynamic data on 50 deg to 74 deg Delta wings on common fuselagePositions of the primary vortex flow reattachment line and longitudinal aerodynamic data were obtained at Mach number 0.3 for a systematic series of vortex flaps on delta wing body configurations with leading edge sweeps of 50, 58, 66, and 74 deg. The investigation was performed to study the parametric effects of wing sweep, vortex flap geometry and deflection, canards, and trailing edge flaps on the location of the primary vortex reattachment line relative to the flap hinge line. The vortex reattachment line was located via surface oil flow photographs taken at selected angles of attack. Force and moment measurements were taken over an angle of attack range of -1 deg to 22 deg at zero sideslip angle for many configurations to further establish the data base and to assess the aforementioned parametric effects on longitudinal aerodynamics. Both the flow reattachment and aerodynamic data are presented.
Document ID
19840005092
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Frink, N. T. (NASA Langley Research Center Hampton, VA, United States)
Huffman, J. K. (NASA Langley Research Center Hampton, VA, United States)
Johnson, T. D., Jr. (Kentron International, Inc.)
Date Acquired
September 4, 2013
Publication Date
December 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-84618
L-15702
NAS 1.15:84618
Accession Number
84N13160
Funding Number(s)
PROJECT: RTOP 505-31-23-07
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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