摘要
为了降低超音速飞行时产生的波阻,通过斜激波基本公式建立了设计马赫数为2的布泽曼双翼翼型,借助CFD软件计算其升阻特性,并与菱形单翼翼型作对比,同时分析了在非设计条件下布泽曼双翼翼型的壅塞问题。结果表明,布泽曼双翼在设计马赫数下,其波阻较传统菱形单翼降低90%,壅塞问题也得到很好地解决。
To reduce the shock waves in supersonic flight, a two-dimensional Busemann airfoil with a de- signed Maeh number 2 is built by using the oblique shock equation. The drag characteristics of this foil are computed with the help of modem computational fluid dynamics （CFD） tools, and the results are compared with that of a diamond supersonic airfoil. Besides, the choked flow problem of the foil at off-de- sign condition is also discussed. It is demonstrated that the wave drag of the Busemann airfoil is reduced by 90% comparing with the diamond airfoil. The choked flow problem is also well resolved.
出处
《航空计算技术》
2013年第4期76-78,共3页
Aeronautical Computing Technique
基金
国防基础科学预研基金项目资助(A2720060290)
关键词
布泽曼翼型
波阻
壅塞
超音速
Busemann airfoil
shock waves drag
choked flow
supersonic
