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Direct simulation of hypersonic transitional flows over blunt slender bodies.

机译：直接模拟钝体上的高超音速过渡流。

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Hypersonic transitional flow has been studied using the Direct Simulation Monte Carlo method. The cylindrically blunted wedge and spherically blunted cone were examined for body half angles of 0;Numerical simulations showed that rarefied gas effects, such as surface temperature jump and velocity slip, exist. Slip conditions were more significant for the axisymmetric cases and the onset of chemical dissociation occurred first for the two-dimensional configuration at 96 km. Comparisons between the numerical simulation and viscous shock-layer calculations at the higher altitudes show significant differences in the calculated heat-transfer rate, body drag and flowfield structure. A comparison with hypersonic wind tunnel heat-transfer rate data showed good agreement.

机译：高超音速过渡流已使用直接模拟蒙特卡洛方法进行了研究。检查了圆柱钝化的楔形体和球形钝化的圆锥体的体半角为0；数值模拟表明，存在稀有气体效应，例如表面温度跳跃和速度滑动。对于轴对称情况，滑移条件更为明显，并且在96 km处的二维结构首先发生化学离解。在较高的高度上，数值模拟与粘性激波层计算之间的比较表明，所计算的传热速率，主体阻力和流场结构存在显着差异。与高超音速风洞传热速率数据的比较显示出很好的一致性。

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作者
Cuda, Vincent, Jr.;
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作者单位

Old Dominion University.;

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授予单位 Old Dominion University.;
学科 Aerospace engineering.
学位 Ph.D.
年度 1987
页码 115 p.
总页数 115
原文格式 PDF
正文语种 eng
中图分类古生物学;
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机译：使用直接模拟蒙特卡洛方法洞察带有气钉的钝体上高超音速稀薄流的流动和传热方面
2. Comparison of High-Altitude Hypersonic Wake Flows of Slender and Blunt Bodies [J] . Jiaqiang Zhong, Takashi Ozawa, Deborah A. Levin AIAA Journal . 2008,第1期

机译：细长体和钝体的高空高超声速尾流比较
3. Direct numerical simulation of hypersonic boundary layer transition over a blunt cone with a small angle of attack [J] . Li XL, Fu DX, Ma YW Physics of fluids . 2010,第2期

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4. AN EFFECTIVE TREATMENT OF NUMERICAL SHOCKWAVE INSTABILITIES WITH RESIDUAL DISTRIBUTION SCHEMES: APPLICATION TO HYPERSONIC FLOWS AROUND BLUNT BODIES. [C] . Jes ′us Garicano Mena, Andrea Lani, Kurt Sermeus, Proceedings of the 7th European symposium on aerothermodynamics. . 2011

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5. A HYPERSONIC THEORY FOR BLUNTED SLENDER BODIES. [D] . ELLINWOOD, JOHN WEBSTER. 1965

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6. Osborne Reynolds pipe flow: Direct simulation from laminar through gradual transition to fully developed turbulence [O] . Xiaohua Wu, Parviz Moin, Ronald J. Adrian, 2015

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7. Direct numerical simulation of hypersonic boundary layer transition over a blunt cone with a small angle of attack [O] . Xinliang Li, Dexun Fu, Yanwen Ma 2010

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8. Investigation of nose bluntness and angle of attack effects on slender bodies in viscous hypersonic flows [R] . Sehgal, A. K., Tiwari, S. N., Singh, D. J. 1991

机译：粘性高超声速流动中细长体的鼻钝和迎角效应研究

Direct simulation of hypersonic transitional flows over blunt slender bodies.

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