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fundamental aerodynamic characteristics of delta wings with leading-edge vortex flowsAn investigation of the aerodynamics of sharp leading-edge delta wings at supersonic speeds has been conducted. The supporting experimental data for this investigation were taken from published force, pressure, and flow-visualization data in which the Mach number normal to the wing leading edge is always less than 1.0. The individual upper- and lower-surface nonlinear characteristics for uncambered delta wings are determined and presented in three charts. The upper-surface data show that both the normal-force coefficient and minimum pressure coefficient increase nonlinearly with a decreasing slope with increasing angle of attack. The lower-surface normal-force coefficient was shown to be independent of Mach number and to increase nonlinearly, with an increasing slope, with increasing angle of attack. These charts are then used to define a wing-design space for sharp leading-edge delta wings.
Document ID
19850053430
Document Type
Reprint (Version printed in journal)
Authors
Wood, R. M.
(NASA Langley Research Center Hampton, VA, United States)
Miller, D. S.
(NASA Langley Research Center High-Speed Aerodynamics Div., Hampton, VA, United States)
Date Acquired
August 12, 2013
Publication Date
June 1, 1985
Publication Information
Publication: Journal of Aircraft
Volume: 22
ISSN: 0021-8669
Subject Category
AERODYNAMICS
Distribution Limits
Public
Copyright
Other