Publication Date:
2019-06-28
Description:
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.
Keywords:
AERONAUTICS (GENERAL)
Type:
NASA-TM-X-2808
,
L-8495
,
NAS 1.15:X-2808
Format:
application/pdf
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