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Theoretical estimation of the transonic aerodynamic characteristics of a supercritical-wing transport model with trailing-edge controlsA method for rapidly estimating the overall forces and moments at supercritical speeds, below drag divergence, of transport configurations with supercritical wings is presented. The method was also used for estimating the rolling moments due to the deflection of wing trailing-edge controls. This analysis was based on a vortex-lattice technique modified to approximate the effects of wing thickness and boundary-layer induced camber. Comparisons between the results of this method and experiment indicate reasonably good correlation of the lift, pitching moment, and rolling moment. The method required much less storage and run time to compute solutions over an angle-of-attack range than presently available transonic nonlinear methods require for a single angle-of-attack solution.
Document ID
19780022113
Document Type
Technical Publication (TP)
Authors
Luckring, J. M. (NASA Langley Research Center Hampton, VA, United States)
Mann, M. J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
August 1, 1978
Subject Category
AERODYNAMICS
Report/Patent Number
NASA-TP-1253
L-11257
Funding Number(s)
PROJECT: RTOP 505-11-16-07
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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