Heat and drag reduction on the nose cone is a significant issue for increasing the speed of the supersonic vehicles. In this paper, computational fluid dynamic method is applied to investigate the thermal and drag coefficient on the sharp nose cone with different cavity shapes. In order to simulate our model, the CFD method with SST turbulence model is applied to study the flow feature and temperature distribution in the vicinity of the nose body. The effect of depth and length of the cavity on the thermal characteristic of the nose cone is comprehensively investigated. In addition, the influence of the number of the cavity in the thermal performance of the main body is studied. According to our results, increasing the length of the cavity highly efficient for the reduction of the drag at Mach = 3. As the Mach number is increased to 3, the number of the cavity becomes a significant role and it is observed that case 9 with four cavities is more efficient. Obtained results also show that increasing the cavity depth declines the temperature on the main body. Our findings confirm that the main source of the expansion is the edge of the cavity.

中文翻译：

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超音速流中尖鼻锥上空腔流动的计算研究

减少鼻锥的热量和阻力是提高超音速飞行器速度的重要问题。本文采用计算流体动力学方法研究了不同腔体形状的尖头锥体的热和阻力系数。为了模拟我们的模型，采用 SST 湍流模型的 CFD 方法研究了鼻体附近的流动特征和温度分布。综合研究了空腔深度和长度对鼻锥热特性的影响。此外，研究了空腔数量对主体热性能的影响。根据我们的结果，增加腔的长度对于减少马赫 = 3 时的阻力非常有效。随着马赫数增加到 3，腔的数量成为一个重要的角色，并且观察到具有四个腔的案例 9 更有效。获得的结果还表明，增加型腔深度会降低主体上的温度。我们的研究结果证实，膨胀的主要来源是空腔的边缘。