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Development of Direct-Inverse 3-D Methods for Applied Transonic Aerodynamic Wing Design and Analysis. Semiannual Progress Report, July 1-December 31, 1988

机译：应用跨音速气动机翼设计与分析的直逆三维方法研究。半年度进展报告，1988年7月1日至12月31日

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Progress in the direct-inverse wing design method in curvilinear coordinates has been made. This includes the remedying of a spanwise oscillation problem and the assessment of grid skewness, viscous interaction, and the initial airfoil section on the final design. It was found that, in response to the spanwise oscillation problem that designing at every other spanwise station produced the best results for the cases presented, a smoothly varying grid is especially needed for the accurate design at the wing tip, the boundary layer displacement thicknesses must be included in a successful wing design, the design of high and medium aspect ratio wings is possible with this code, and the final airfoil section designed is fairly independent of the initial section.

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作者
Carlson, L. A.;
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年度 1989
页码 p.1-85
总页数 85
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
Aircraft design; Airfoils; Computer programs; Transonic speed; Wings; Aspect ratio; Spherical coordinates; Three dimensional models;

机译：飞机设计;翼型;计算机程序;跨音速;翼;纵横比;球面坐标;三维模型;

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4. Development of Direct-Inverse 3-D Methods for Applied Aerodynamic Design and Analysis. Semiannual Progress Report, July 1-December 31, 1987 [R] . Carlson, L. A. 1988

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Development of Direct-Inverse 3-D Methods for Applied Transonic Aerodynamic Wing Design and Analysis. Semiannual Progress Report, July 1-December 31, 1988

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