【作者】 尚伟烈；

【导师】 赵润祥；

【作者基本信息】 南京理工大学 ， 流体力学， 2004， 硕士

【摘要】 本文主要对滑翔增程弹气动力工程计算进行了研究。应用McCoy经验方法、牛顿修正方法、Van-Driest方法、κpachob,H.X经验方法、Moore等经验方法与小扰动理论、锥形流理论、升力面理论相结合，给出弹体，弹翼，尾翼和全弹气动力工程计算方法。根据这套算法，作者编制了相应的计算程序，对122mm火箭弹、250kg航空杀爆炸弹和某滑翔增程弹的Ⅰ、Ⅱ两种型号进行了计算，计算结果符合空气动力学规律。通过对比两种型号的滑翔增程弹计算结果，分析了来流马赫数、攻角和弹翼对滑翔增程弹气动特性影响。该方法满足了滑翔增程弹气动力设计计算的要求。更多还原

【Abstract】 This thesis presents the empirical method for prediction the aerodynamic coefficients on glide bullet. McCoy empirical method , Newton method , Van-Driest method , Kpachob,H.X empirical method, Moore empirical method is applied and except these empirical, the little disturbing theory, taper flow theory , lifting surface theory are also applied. Through these theory and empirical method, this thesis presents a suit of methods to calculate the aerodynamic characteristics of the body alone , tail alone , wing alone and the wing-body-tail combination at subsonic , transonic , and supersonic, bases these methods, author has developed the computation program. Three calculation example are used in this thesis, they are 122mm-missile bullet,250kg aviation bomb and a glide bullet with I,II two models. The aerodynamic coefficients results of the calculation were coherent with the result of the wind tunnel experiments, through the comparing the result of the two models of the glide bullet, the affect of the Mach number, the angle of attack and the wing on aerodynamic characteristics of glide bullet is analyzed, this set of methods are suitable for the calculation of the glide bullet.更多还原