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首页> 外文期刊>Journal of Beijing Institute of Technology >Wind Tunnel Experimental Investigation on the Aerodynamic Characteristics of the Multifin Rockets and Missiles
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Wind Tunnel Experimental Investigation on the Aerodynamic Characteristics of the Multifin Rockets and Missiles

机译：多翅火箭弹气动特性的风洞实验研究

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摘要

The transonic-supersonic wind tunnel experiment on the aerodynamics of the rockets and missiles that have four, six, eight flat or wrap-around fins is introduced. The experimental results show, while M_∞ < 2.0, with the increase of the fins' number, the derivative of lift coefficient is increasing, the pressure center is shifting backwards, and the longitudinal static stability is augmenting. On the contrary, while the Mach number exceeds a certain supersonic value, the aerodynamic effectiveness of the eight-fin missiles would be lower than that of the six-fin missiles. For the low speed short-range missiles, by adopting six, eight or ten flat fins configuration, the lift effectiveness can be greatly increased, the pressure center can be shifted backwards, the static and dynamic stability can be obviously enhanced. For the high speed long-range large rockets and missiles launched from multi-tube launcher, the configuration adopting more than six fins can not be useful for increasing the stability but would make the rolling rate instable during the flight.
机译：进行了跨音速-超音速风洞实验，研究了具有四个，六个，八个扁平或环绕式鳍片的火箭和导弹的空气动力学特性。实验结果表明，当M_∞<2.0时，随着翅片数的增加，升力系数的导数增加，压力中心向后移动，纵向静力稳定性增强。相反，尽管马赫数超过一定的超音速值，但八鳍导弹的空气动力学效率将低于六鳍导弹。对于低速近程导弹，采用六个，八个或十个扁平鳍片配置，可以大大提高升力效果，可以使压力中心向后移动，可以明显提高静，动态稳定性。对于从多管发射器发射的高速远程大型火箭和导弹，采用六个以上鳍片的配置虽然不能用于增加稳定性，但会使飞行过程中的滚动速度不稳定。

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