亚、超音速细长翼身组合体大迎角气动特性的计算研究

Study on Calculating the Subsonic and SupersonicAerodynamic Characteristics of Slender Wing-BodyCombinations at Large Angles of Attack

本文提出了一种适于初步设计使用、具有良好精度的亚、超音速细长翼身组合体大迎角气动特性的综合性计算方法。对大迎角情况下的涡升力,采用吸力比拟原理计算;位流升力的计算,采用基本解的数值计算方法。关于机翼翼剖面头部圆度和涡破碎对涡升力的影响,进行经验性修正。翼身干扰的贡献,通过翼身干扰系数进行计算。并按文[4]原理,将亚音速计算方法推广到亚音速前缘的超音速情况。对几种机翼与翼身组合体的计算结果表明,本文方法具有方法简便、计算快速和符合设计精度要求的优点。

This paper presents a calculation method of subsonic and supersonic aerodynamic characteristics of slender wing-body combinations at large angles of attack,which has highly accurate results in calculation,and may be applicable to the first design of missiles and aircraft. The vortex lift at a large angle of attack is calculated by the suction analogy principle. The potential lift is computed by the numerical method of basic solution distribution. The effects of round leading-edge and vortex-breakdown on vortex lift of the wings is determined from empirical method. The contribution of body carry-over effects on aerodynamic characteristics of wing-body combination is considered by interference coefficients of wing-body combination. Based on the principle of Ref. [4],the calculation method of Ref. [9] in the subsonic speed region is extended to the supersonic speed region. The method presented in this paper has the advantages of rapid and accurate calculation of the aerodynamic characteristics of a wing or wing-body combination through comparisons of the calculated results with experimental data for several wings and a wing-body combination.