AERODYNAMIC DESIGN OF SUPERSONIC CRUISE WINGS WITH A CALIBRATED LINEARIZED THEORY

被引：5

作者：

MANN, MJ

CARLSON, HW

机构：

[1] NASA Langley Research Center, Vehicle Integration Branch, Advanced Vehicles Division, MS 412, Hampton, VA

[2] Lockheed Engineering and Sciences Company, Hampton, VA

[3] LoAdvanced Aircraft Branch, Advanced Vehicles Division, NASA Langley Research Center, MS 411, Hampton, VA

来源：

JOURNAL OF AIRCRAFT | 1994年 / 31卷 / 01期

关键词：

651.1; Aerodynamics; General; -; 652.1; Aircraft; General - 652.3 Aircraft Instruments and Equipment - 921.6 Numerical Methods;

D O I：

10.2514/3.46452

中图分类号：

V [航空、航天];

学科分类号：

08 ; 0825 ;

摘要：

The design of supersonic cruise wings for minimum drag due to lift is examined in this study. The aerodgnamic design method is based on a supersonic linearized theory modified to include corrections for attainable leading-edge thrust and vortex forces. A semiempirical design and estimation method has been developed to account for the deficiencies of the linearized theory which tends to overestimate the required amount of twist and camber and predicts an unattainable level of performance. Comparisons of theoretical and experimental results showed that the semiempirical method provides for the selection of the amount of twist and camber required for maximum performance at cruise and gives a good estimate of the level of performance.

引用

页码：35 / 41

页数：7

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