Drag Reduction and Aerodynamic Shape Optimization for Spike-Tipped Supersonic Blunt Nose

Xue Yuan; Wang Liang; Fu Song

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Drag Reduction and Aerodynamic Shape Optimization for Spike-Tipped Supersonic Blunt Nose

机译：尖峰超音速钝鼻的减阻和空气动力学形状优化

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A space vehicle in atmosphere travels mostly at supersonic speed and generates a very strong bow shock wave around its blunt nose. This causes a large high-pressure area at the front nose surface accompanied with high temperature. It suggests high-pressure drag and high risk of heat shield failure. Oblique shock and conical separated flow zone generated by a forward disk-tip spike significantly reduce the drag by reducing the high-pressure area on the blunt nose. In the present work, aerodynamics of the high-speed spike-tipped blunt nose is investigated here numerically with Mach number up to 4.5. It is highlighted here that there exists an optimal combination of spike length and disk-tip diameter giving rise to minimal drag at supersonic speed. The reason for drag reduction is analyzed in detail.

机译：太空中的航天器通常以超音速行进，并在钝头周围产生非常强的弓形冲击波。这会在前鼻表面产生较大的高压区域，并伴有高温。这表明存在高压阻力，并且隔热板故障的风险很高。向前的圆盘尖刺产生的倾斜冲击和圆锥形分离的流动区域通过减小钝头上的高压区域而显着减少了阻力。在目前的工作中，这里对高速尖刺钝嘴的空气动力学进行了数值研究，其马赫数最高为4.5。这里要强调的是，存在尖峰长度和圆盘尖端直径的最佳组合，从而在超音速下产生最小的阻力。详细分析了减少阻力的原因。

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来源
《Journal of Spacecraft and Rockets》 |2018年第3期|552-560|共9页
作者
Xue Yuan; Wang Liang; Fu Song;
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作者单位

Tsinghua Univ, Sch Aerosp Engn, Beijing 100084, Peoples R China;

Tsinghua Univ, Sch Aerosp Engn, Beijing 100084, Peoples R China;

Tsinghua Univ, Sch Aerosp Engn, Beijing 100084, Peoples R China;

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收录信息美国《科学引文索引》(SCI);美国《工程索引》(EI);
原文格式 PDF
正文语种 eng
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Drag Reduction and Aerodynamic Shape Optimization for Spike-Tipped Supersonic Blunt Nose

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