NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Collections About News Help Login
Back to Results
Estimated Benefits of Variable-Geometry Wing Camber Control for Transport AircraftAnalytical benefits of variable-camber capability on subsonic transport aircraft are explored. Using aerodynamic performance models, including drag as a function of deflection angle for control surfaces of interest, optimal performance benefits of variable camber are calculated. Results demonstrate that if all wing trailing-edge surfaces are available for optimization, drag can be significantly reduced at most points within the flight envelope. The optimization approach developed and illustrated for flight uses variable camber for optimization of aerodynamic efficiency (maximizing the lift-to-drag ratio). Most transport aircraft have significant latent capability in this area. Wing camber control that can affect performance optimization for transport aircraft includes symmetric use of ailerons and flaps. In this paper, drag characteristics for aileron and flap deflections are computed based on analytical and wind-tunnel data. All calculations based on predictions for the subject aircraft and the optimal surface deflection are obtained by simple interpolation for given conditions. An algorithm is also presented for computation of optimal surface deflection for given conditions. Benefits of variable camber for a transport configuration using a simple trailing-edge control surface system can approach more than 10 percent, especially for nonstandard flight conditions. In the cruise regime, the benefit is 1-3 percent.
Document ID
19990090019
Acquisition Source
Armstrong Flight Research Center
Document Type
Technical Memorandum (TM)
Authors
Bolonkin, Alexander (National Academy of Sciences - National Research Council Washington, DC United States)
Gilyard, Glenn B. (NASA Dryden Flight Research Center Edwards, CA United States)
Date Acquired
September 6, 2013
Publication Date
October 1, 1999
Subject Category
Aerodynamics
Report/Patent Number
NASA/TM-1999-206586
H-2368
NAS 1.15:206586
Funding Number(s)
PROJECT: RTOP 522-16-14-00-39
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available