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Numerical investigation of hypersonic flow over a forward-facing cavity.

机译:超音速流在前腔上的数值研究。

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There are two main objectives of this work: (1) to determine if and how the presence of a forward-facing axial cavity in a blunt nose can reduce surface heating rates compared to a blunt body without a cavity, and (2) to describe the fluid dynamics of these unsteady flows. A commercial finite-volume computer code was used to produce steady and unsteady time-accurate numerical simulations. Numerical simulation results were often directly compared to recent experiments.; The initial study focused on the surface heating and flowfield structure of steady cavity flows. Sharp lips were found to produce both a recirculation region which 'cools' the outer surface, and severe heating just inside the cavity. Rounding the lip eliminates the recirculation region and alleviates heating inside the cavity. It was concluded that the steady cavity flow does not present a surface heat reduction compared with blunt nose shapes.; Subsequent study focused on unsteady cavity flows. A new nose-tip surface heat reduction mechanism was discovered. Substantial surface nose-tip cooling is achieved by creating strong longitudinal pressure oscillations within the cavity to induce large bow shock oscillations. Due to the motion of the bow shock relative to the body, the mean stagnation temperature of the air flow into the cavity is reduced. The cooling benefit increases with mean bow shock oscillation. This mechanism has been further validated by experiment. The cooling mechanism is not effective in very deep cavities since the bow shock exhibits only long period oscillation. The design implications of using a nose-cavity for surface heat reduction in a hypersonic penetrator are briefly addressed.; A parameter study was conducted to study the mechanisms of resonance. Resonant pressure oscillations within the cavity occur for relatively shallow cavities provided freestream noise is present. However, deeper cavities self-sustain strong resonance. A spring-mass-damper model is described which emulates noise-driven, relatively shallow cavity acoustic behavior. An extensive parametric study of relatively-shallow cavities driven by freestream noise was conducted to better understand the unsteady fluid dynamics and verify the spring-mass-damper model.
机译:这项工作有两个主要目标:(1)确定钝头中是否存在前向轴向腔以及与没有腔的钝体相比是否可以降低表面加热速率,以及(2)描述这些不稳定流动的流体动力学。商业有限体积的计算机代码用于产生稳定和不稳定的时间精确的数值模拟。数值模拟结果经常直接与最近的实验进行比较。最初的研究集中在稳定腔流的表面加热和流场结构上。发现锋利的嘴唇会产生“冷却”外表面的回流区域,以及在腔体内产生严重的热量。使嘴唇变圆消除了再循环区域并减轻了腔体内的热量。得出的结论是,与钝头形状相比,稳定的腔体流动不会降低表面热量。随后的研究集中于不稳定的腔体流动。发现了一种新的鼻尖表面降温机理。通过在型腔内产生强烈的纵向压力振荡来引起大的弓形激波振荡,可以实现对表面的大量鼻尖冷却。由于弓形冲击相对于身体的运动,流入空腔的空气的平均停滞温度降低了。冷却效果随平均弓形振动的增加而增加。该机制已通过实验进一步验证。由于弓形冲击仅表现出长时间的振荡,因此冷却机制在非常深的空腔中无效。简要介绍了在高超声速穿透器中使用鼻腔降低表面热量的设计意义。进行了参数研究以研究共振机理。如果存在自由流噪声,则相对较浅的空腔会在空腔内发生谐振压力振荡。但是,更深的空腔会自我维持强烈的共振。描述了一种弹簧质量阻尼器模型,该模型模拟了噪声驱动的相对较浅的腔体声学行为。对自由流噪声驱动的相对较浅的腔进行了广泛的参数研究,以更好地了解不稳定流体动力学并验证弹簧质量阻尼器模型。

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