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aero-mechanical design methodology for subsonic civil transport high-lift systemsIn today's highly competitive and economically driven commercial aviation market, the trend is to make aircraft systems simpler and to shorten their design cycle which reduces recurring, non-recurring and operating costs. One such system is the high-lift system. A methodology has been developed which merges aerodynamic data with kinematic analysis of the trailing-edge flap mechanism with minimum mechanism definition required. This methodology provides quick and accurate aerodynamic performance prediction for a given flap deployment mechanism early on in the high-lift system preliminary design stage. Sample analysis results for four different deployment mechanisms are presented as well as descriptions of the aerodynamic and mechanism data required for evaluation. Extensions to interactive design capabilities are also discussed.
Document ID
20000061426
Document Type
Conference Paper
Authors
vanDam, C. P.
(California Univ. Davis, CA United States)
Shaw, S. G.
(California Univ. Davis, CA United States)
VanderKam, J. C.
(California Univ. Davis, CA United States)
Brodeur, R. R.
(California Univ. Davis, CA United States)
Rudolph, P. K. C.
(PKCR, Inc. Seattle, WA United States)
Kinney, D.
(NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
August 19, 2013
Publication Date
June 1, 2000
Publication Information
Publication: Aerodynamic Design and Optimisation of Flight Vehicles in a Concurrent Multi-Disciplinary Environment
Subject Category
Aircraft Design, Testing and Performance
Funding Number(s)
CONTRACT_GRANT: A46374D(LAS)
CONTRACT_GRANT: SNL-A0273
CONTRACT_GRANT: A49736D(SLS)
CONTRACT_GRANT: NCC2-5255
CONTRACT_GRANT: NCC2-5188
Distribution Limits
Public
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