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Lee-side flow over delta wings at supersonic speedsAn experimental investigation of the lee-side flow on sharp leading-edge delta wings at supersonic speeds has been conducted. Pressure data were obtained at Mach numbers from 1.5 to 2.8, and three types of flow-visualization data (oil-flow, tuft, and vapor-screen) were obtained at Mach numbers from 1.7 to 2.8 for wing leading-edge sweep angles from 52.5 deg to 75 deg. From the flow-visualization data, the lee-side flows were classified into seven distinct types and a chart was developed that defines the flow mechanism as a function of the conditions normal to the wing leading edge, specifically, angle of attack and Mach number. Pressure data obtained experimentally and by a semiempirical prediction method were employed to investigate the effects of angle of attack, leading-edge sweep, and Mach number on vortex strength and vortex position. In general, the predicted and measured values of vortex-induced normal force and vortex position obtained from experimental data have the same trends with angle of attack, Mach number, and leading-edge sweep; however, the vortex-induced normal force is underpredicted by 15 to 30 percent, and the vortex spanwise location is overpredicted by approximately 15 percent.
Document ID
19850021609
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Miller, D. S. (NASA Langley Research Center Hampton, VA, United States)
Wood, R. M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
June 1, 1985
Subject Category
Aerodynamics
Report/Patent Number
L-15888
NASA-TP-2430
NAS 1.60:2430
Accession Number
85N29921
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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