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The 'limiting line' in mixed subsonic and supersonic flow of compressible fluids

机译:可压缩流体在亚音速和超音速混合流中的“极限线”

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摘要

It is well known that the vorticity for any fluid element is constant if the fluid is non-viscous and the change of state of the fluid is isentropic. When a solid body is placed in a uniform stream, the flow far ahead of the body is irrotational. Then if the flow is further assumed to be isentropic, the vorticity will be zero over the whole filed of flow. In other words, the flow is irrotational. For such flow over a solid body, it is shown by Theodorsen that the solid body experiences no resistance. If the fluid has a small viscosity, its effect will be limited in the boundary layer over the solid body and the body will have a drag due to the skin friction. This type of essentially isentropic irrotational flow is generally observed for a streamlined body placed in a uniform stream, if the velocity of the stream is kept below the so-called "critical speed." At the critical speed or rather at a certain value of the ratio of the velocity of the undisturbed flow and the corresponding velocity of sound, shock waves appear. This phenomenon is called the "compressibility bubble." Along a shock wave, the change of state of the fluid is no longer isentropic, although still adiabatic. This results in an increase in entropy of the fluid and generally introduces vorticity in an originally irrotational flow. The increase in entropy of the fluid is, of course, the consequence of changing part of the mechanical energy into heat energy. In other words, the part of fluid affected by the shock wave has a reduced mechanical energy. Therefore, with the appearance of shock waves, the wake of the streamline body is very much widened, and the drag increases drastically. Furthermore, the accompanying change in the pressure distribution over the body changes the aerodynamic moment acting on it and in the case of an airfoil decreases the lift force. All these consequences of the breakdown of isentropic irrotational flow are generally undesirable in applied aerodynamics. Its occurrence should be delayed as much as possible by modifying the shape or contour of the body. However, such endeavor will be very much facilitated if the cause or the criterion for the breakdown can be found first.
机译:众所周知,如果流体是非粘性的并且流体状态的变化是等熵的,则任何流体元件的涡度都是恒定的。当将固体均匀地放置在水流中时,远远超出该物体的水流是无旋转的。然后,如果进一步假设流动是等熵的,则在整个流动领域中,涡度将为零。换句话说,流动是无旋转的。对于在固体上的这种流动,塞奥多尔森(Theodorsen)表明,固体没有阻力。如果流体的粘度较小,则其作用将限制在固体主体的边界层中,并且由于皮肤摩擦,主体将具有阻力。如果将流线速度保持在所谓的“临界速度”以下,通常会观察到放置在均匀流中的流线型主体的这种基本等熵的无旋流。在临界速度下,或更确切地说,在未扰动流速度与相应声速之比的某个值处,会出现冲击波。这种现象称为“可压缩性气泡”。沿着冲击波,流体的状态变化不再是等熵的,尽管仍然是绝热的。这导致流体的熵增加,并且通常在最初的非旋流中引入涡旋。当然,流体熵的增加是将部分机械能变为热能的结果。换句话说,受到冲击波影响的流体部分具有减小的机械能。因此,随着冲击波的出现,流线体的尾流大大加宽,阻力急剧增加。此外,伴随在车身上的压力分布的变化改变了作用在车身上的空气动力力矩,并且在机翼的情况下减小了升力。等熵旋转流破裂的所有这些后果在应用空气动力学中通常是不希望的。通过修改身体的形状或轮廓,应尽可能延迟其出现。但是,如果可以首先找到故障的原因或判据,则将极大地促进这种努力。

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    Tsien, Hsue-Shen;

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  • 年度 1944
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