Aeroheating around hypersonic vehicle is a very critical phenomenon and should be taken into account during design of the hypersonic vehicles. High Temperature at high speed reentry vehicles, mars and lunar shuttle is very critical to predict and calculate from the structural and thermal point of view. Mars and Venus exploration programs are under progress. Speed of hypersonic vehicle is very high so causes highly chemically reacting flow which produce some other phenomena in the boundary layers. So heat flux should be taken into account. Entropy layer become very critical in boundary layer. Normally these configurations have cone cylinder and frustum body so recirculation zone and reattachment zone are very important to simulate and calculate the flow parameters. In this paper two dimensional and three dimensional hypersonic viscous fiowfield around a half cylinder, cone and Mars Aeroshell have been simulated and analyzed to predict the flow parameters. Boundary layers and wake regions are specially simulated by using very high mesh density in the same region. Different angles of attack are used to study the flow behavior. In the first part of work two-dimensional geometries are simulated to study the hypersonic flows. Mach number 6 and 16.34 are simulated on cone and half cylinder to study the heat transfer and surface temperature variation. Three-dimensional simulations are performed to clarify the effect of high temperature phenomena on the aerodynamic characteristics of Mars aeroshell geometry. The calculated aerodynamic coefficients are compared with the experimental data obtained in the hypersonic wind tunnel test. At very high Mach number the flow is squeezed to the surface with low density flow and high temperature. Boundary layers are very thin and squeezed towards wall so create high temperature flow. Which causes flow species to react chemically and change the aerodynamics of flow and its effect on body.so Mars aeroshell is simulated against frozen flow assumption and chemical reactions are added to study the thermochemical effects on the body. Turbulent models and DES are used to simulate such type of hypersonic flow with chemical reactions.
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机译：超音速车辆周围的空气是一种非常关键的现象，在超音速车辆的设计期间应考虑到。高速再入车辆的高温，火星和月球航天飞机对于预测和计算结构和热的观点来说非常重要。火星和金星勘探计划正在进行中。高超速度的速度非常高，因此在边界层中产生高度化学反应的流动，在边界层中产生一些其他现象。因此，应考虑热量。熵层在边界层变得非常关键。通常，这些配置具有锥形圆筒和截头体，因此再循环区域和重新附接区非常重要，以模拟和计算流量参数。在本文中，已经模拟并分析了围绕半气缸，锥形和火星雾化的二维和三维高超声粘的电影管道以预测流量参数。通过在同一区域中使用非常高的网状密度来特别模拟边界层和唤醒区域。使用不同的攻击角度来研究流动行为。在工作的第一部分中，模拟了二维几何形状以研究超声波流动。 Mach Number 6和16.34在锥形和半气缸上模拟，以研究传热和表面温度变化。进行三维模拟，以阐明高温现象对火星气动几何空气动力学特性的影响。将计算出的空气动力学系数与在超声波风隧道试验中获得的实验数据进行比较。在非常高的Mach编号，流量被挤压到表面的低密度和高温。边界层非常薄，挤向墙壁，因此产生高温流动。这使得流量物种化学反应并改变流动的空气动力学及其对体内的影响。因此，模拟冻结流动假设和化学反应的模拟MARS Aeroshels，以研究对体内的热化学作用。湍流型号和DES用于模拟这种类型的高超声流，具有化学反应。
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