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Survey and analysis of research on supersonic drag-due-to-lift minimization with recommendations for wing designA survey of research on drag-due-to-lift minimization at supersonic speeds, including a study of the effectiveness of current design and analysis methods was conducted. The results show that a linearized theory analysis with estimated attainable thrust and vortex force effects can predict with reasonable accuracy the lifting efficiency of flat wings. Significantly better wing performance can be achieved through the use of twist and camber. Although linearized theory methods tend to overestimate the amount of twist and camber required for a given application and provide an overly optimistic performance prediction, these deficiencies can be overcome by implementation of recently developed empirical corrections. Numerous examples of the correlation of experiment and theory are presented to demonstrate the applicability and limitations of linearized theory methods with and without empirical corrections. The use of an Euler code for the estimation of aerodynamic characteristics of a twisted and cambered wing and its application to design by iteration are discussed.
Document ID
19920024412
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Carlson, Harry W. (Lockheed Engineering and Sciences Co. Hampton, VA., United States)
Mann, Michael J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
September 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.60:3202
NASA-TP-3202
L-16963
Accession Number
92N33656
Funding Number(s)
PROJECT: RTOP 505-68-70-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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