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Simulator study of the stall departure characteristics of a light general aviation airplane with and without a wing-leading-edge modificationA six-degree-of-freedom nonlinear simulation was developed for a two-place, single-engine, low-wing general aviation airplane for the stall and initial departure regions of flight. Two configurations, one with and one without an outboard wing-leading-edge modification, were modeled. The math models developed are presented simulation predictions and flight-test data for validation purposes and simulation results for the two configurations for various maneuvers and power settings are compared to show the beneficial influence of adding the wing-leading-edge modification.
Document ID
19850016939
Document Type
Technical Memorandum (TM)
Authors
Riley, D. R. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
May 1, 1985
Subject Category
AIRCRAFT DESIGN, TESTING AND PERFORMANCE
Report/Patent Number
L-15792
NASA-TM-86309
NAS 1.15:86309
Funding Number(s)
PROJECT: RTOP 505-45-43
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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