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Full-scale wind-tunnel investigation of the effects of wing leading-edge modifications on the high angle-of-attack aerodynamic characteristics of a low-wing general aviation airplaneThe paper presents the results of a recent investigation to determine the effects of wing leading-edge modifications on the high angle-of-attack aerodynamic characteristics of a low-wing general aviation airplane in the Langley Full-Scale Wind Tunnel. The investigation was conducted to provide aerodynamic information for correlation and analysis of flight-test results obtained for the configuration. The wind-tunnel investigation consisted of force and moment measurements, wing pressure measurements, flow surveys, and flow visualization studies utilizing a tuft grid, smoke and nonintrusive mini-tufts which were illuminated by ultra-violet light. In addition to the tunnel scale system which measured overall forces and moments, the model was equipped with an auxiliary strain-gage balance within the left wing panel to measure lift and drag forces on the outer wing panel independent of the tunnel scale system. The leading-edge modifications studied included partial- and full-span leading-edge droop arrangements as well as leading-edge slats.
Document ID
19800059132
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Johnson, J. L., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Newsom, W. A.
(NASA Langley Research Center Hampton, VA, United States)
Satran, D. R.
(NASA Langley Research Center Hampton, Va., United States)
Date Acquired
August 10, 2013
Publication Date
August 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 80-1844
Meeting Information
Meeting: Aircraft Systems Meeting
Location: Anaheim, CA
Start Date: August 4, 1980
End Date: August 6, 1980
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
80A43302
Distribution Limits
Public
Copyright
Other

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