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首页> 外文学位 >Effects of nose bluntness and shock-shock interactions on blunt bodies in viscous hypersonic flows.
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Effects of nose bluntness and shock-shock interactions on blunt bodies in viscous hypersonic flows.

机译：鼻子过钝和电击-相互作用对粘性高超声速流动中钝体的影响。

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摘要

A numerical study has been conducted to investigate the effects of blunt leading edges on the viscous flow field around a hypersonic vehicle such as the proposed National Aero-Space Plane. Attention is focused on two specific regions of the flow field. Analysis of these flow regions is required to accurately predict the overall flow field as well as to get necessary information on localized zones of high pressure and intense heating.; The forebody is modeled by slender cones and ogives with spherically blunted nose. A combination of Navier-Stokes and parabolized Navier-Stokes equations is used to compute the flow field. The influence of entropy layer thickness on the extent of the leading edge effects is also considered. The extent of downstream effects of leading edge thickness are determined at Mach numbers of 10 and 20 for cone angles of 5{dollar}spcirc{dollar}, 10{dollar}spcirc{dollar}, and 20{dollar}spcirc{dollar}. Three values of nose bluntness are considered with the smallest nose blunting (0.0025m) representing the sharp cone/ogive.; For the flow region around the inlet the forebody shock can interact either with the blunt cowl leading edge shock or with the shock produced by the blunt leading edges of the swept sidewall compression surfaces of the inlet. For the interaction at the cowl leading edge, the forebody shock is assumed planar and the cowl is modeled by a two-dimensional cylindrically blunted wedge of infinite width. Use of the full Navier-Stokes equations is made on the cowl forebody and the thin-layer Navier-Stokes equations are suitably modified for space marching on the cowl afterbody. The results of the study show that the flow around the cowl is significantly altered by the impinging shock. The peak value of pressure is found to be nine times and heating rates eight times the stagnation point value for unimpinged case at Mach 8.03. The peak values were slightly lower for Mach 5.94 calculations. A three-dimensional thin-layer Navier-Stokes code has been used to calculate the flow field. The peak pressure for this case is found to be 2.25 times and the peak heating three times the unimpinged stagnation values. The results of the study are compared with the available experimental and numerical results. (Abstract shortened with permission of author.)
机译：已经进行了数值研究，以研究钝化的前缘对高超声速飞行器（如拟议中的国家航空航天飞机）周围的粘性流场的影响。注意集中在流场的两个特定区域。需要对这些流动区域进行分析，以准确地预测整体流场，并获得有关高压和强烈加热的局部区域的必要信息。前体的造型是细长的圆锥形和带球形钝鼻的钝齿。 Navier-Stokes和抛物线化的Navier-Stokes方程的组合用于计算流场。还考虑了熵层厚度对前缘效应的程度的影响。对于5 {，10 10和20 20的锥角，前缘厚度的下游影响程度在马赫数为10和20时确定。鼻子钝度的三个值被认为是最小的鼻子钝角（0.0025m），代表尖锐的圆锥形。对于入口周围的流动区域，前体冲击可以与钝的前围前缘冲击或与入口的后掠侧壁压缩表面的钝的前边缘产生的冲击相互作用。对于前围前缘的相互作用，假定前体冲击是平面的，并且前围由无限宽度的二维圆柱钝钝楔建模。在前围前体上使用完整的Navier-Stokes方程式，并对下层Navier-Stokes方程进行适当修改，以在前围后体上进行空间行进。研究结果表明，撞击冲击显着改变了前围周围的气流。对于8.03马赫的无冲击情况，发现压力峰值是停滞点值的九倍，加热速率是停滞点值的八倍。对于5.94马赫计算，峰值略低。三维薄层Navier-Stokes代码已用于计算流场。在这种情况下，发现峰值压力为2.25倍，峰值加热为未受阻滞止值的三倍。将研究结果与可用的实验和数值结果进行比较。 （摘要经作者许可缩短。）

著录项

  • 作者

    Singh, Dal Jeet.;

  • 作者单位

    Old Dominion University.;

  • 授予单位 Old Dominion University.;
  • 学科 Engineering Mechanical.
  • 学位 Ph.D.
  • 年度 1989
  • 页码 186 p.
  • 总页数 186
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 机械、仪表工业;
  • 关键词

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