Wind-tunnel investigation of vortex flaps on a highly swept interceptor configurationA subsonic wind-tunnel investigation of the application of vortex flaps to a supersonic interceptor configuration is described. Experimental results are presented which indicate the aerodynamic effects of vortex-flap deflection, trailing-edge flap deflection, vortex flap chord and span, vertical stabilizers, and a highly cambered leading edge designed for attached flow. Data presented include longitudinal forces and moments, upper-surface pressure distributions, and oil- and smoke-flow visualization photographs. It is concluded that a full-span deployable vortex flap can provide a substantial performance improvement for this and other similar configurations.
Document ID
19820057469
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Schoonover, W. E., Jr. (NASA Langley Research Center Hampton, VA, United States)
Ohlson, W. E. (Boeing Military Airplane Co. Seattle, WA, United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1982
Subject Category
Aerodynamics
Meeting Information
Meeting: International Council of the Aeronautical Sciences