Calculation of Shock Shapes over Sharp Cone in Intermediate Hypersonic Airè ow
Calculation of Shock Shapes over Sharp Cone in Intermediate Hypersonic Airè ow
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中高超声速气流中尖锥激波形状的计算
DOI：
10.2514/2.6758
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发表时间：
2003
期刊：
影响因子：
--
通讯作者：
K. Sawada
中科院分区：
文献类型：
--
作者：
M. Furudate;S. Nonaka;K. Sawada
计算了中高超声速流域中锐锥体上的激波形状，以检验现有两温热化学模型的有效性。计算中考虑了两种不同的顶角：一种半角为 30 度，另一种为 45 度。这些几何形状的计算是在大约 3.0 km/s 的八个速度下针对几个不同的静压值进行的。将计算出的冲击层厚度与弹道范围内获得的相应实验数据进行比较。结果表明，双温模型很好地再现了没有化学反应和振动激励的流动条件下的实验数据，但计算出的激波层厚度往往比开始发生振动激励的流动条件下的实验数据更薄。这表明振动弛豫与较薄的冲击层有密切的关系。这项研究证实了我们之前的结果，即在使用现有的双温度模型进行计算时，在相同速度范围内球体上的激波层厚度可能会被低估。
Shock shapes over a sharp cone in the intermediate hypersonic e ow regime are calculated to examine the validity of the existing two-temperature thermochemical model. Two different apex angles are considered in the calculations: one with a half-angle of 30 deg and the other with 45 deg. The calculations for these geometries are carried out for several different static pressure values at the e ight velocity of about 3.0 km/s. The calculated shock layer thickness is compared with the corresponding experimental data obtained in a ballistic range. The resultsshowthatthetwo-temperaturemodelwellreproducestheexperimentaldataforthee owconditionsinwhich chemicalreactionsaswellasvibrational excitationsareabsent.However,thecalculated shock layerthicknesstends to be thinner than the experimental data for the e ow conditions in which vibrational excitation begins to occur. It is implied that vibrational relaxation has a close connection with the thinner shock layer. The study cone rms our previous results that the shock layer thickness over a sphere in the same velocity range can be underestimated in the calculation using the existing two-temperature model.
强冲击波后N2旋转弛豫的实验研究
DOI：
--
发表时间：
2008
期刊：
影响因子：
--
作者：
Yamada;G.
通讯作者：
G.