A program for the wind tunnel development of underwing leading-edge vortex generators on an NASA supercritical-wing research airplane model was conducted in the Langley 8-foot transonic pressure tunnel at Mach numbers from 0.25 to 0.99. The effects on the longitudinal aerodynamic characteristics of vortex-generator wing semispan location, distance from wing leading edge, leading-edge sweep angle, toe-in angle, and span are presented. The effects of the vortex generators on the lateral-directional aerodynamic characteristics of the model for a sideslip angle of 5 deg are included.
Wind-Tunnel Development of Underwing Leading-Edge Vortex Generators on a NASA Supercritical-Wing Research Airplane Configuration
1973
118 pages
Report
No indication
English
Development of Wing Leading Edge Vortex Generators for a Single Engine General Aviation Airplane
SAE Technical Papers | 1983
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