Numerical Simulation Over Flat-Disk Aerospike at Mach 6

2018 IEEE International Conference on System, Computation, Automation and Networking (ICSCA) Pub Date : 2018-07-01 DOI:10.1109/ICSCAN.2018.8541144

R. S. Pawar, N. Gilke, Vivek P. Warade

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Abstract

Hypersonic missiles combine the speed of ballistic missiles along with the accuracy and maneuverability of cruise missiles. By traveling at hypersonic speed in the atmosphere, blunt nose of missile experiences great surface heating and a large amount of drag. This drag force can be minimized by implementing a structure known as aerospike. This spike is attached in front of the body that significantly changes the flow field and manipulates aerodynamic drag at hypersonic speeds. In the current paper, the effect of implementation a flat-disk aerospike for various L/D (Length to Diameter) ratios is investigated by using computational fluid dynamics (CFD) approach. The CFD analysis is performed to study the effect of drag, lift and pitching moment coefficient onto the blunt body with and without implementation of an aerospike. However, the addition of a flat-disk aerospike in front of the blunt body has an advantage for the reduction in drag subjected to angle of attack but increase in pitching moment has to be taken into consideration.

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6马赫平盘式气动尖峰的数值模拟

高超音速导弹结合了弹道导弹的速度以及巡航导弹的精度和机动性。导弹钝头在大气层中以高超声速飞行时，表面受热较大，阻力较大。这种阻力可以通过采用一种被称为气钉的结构来最小化。这个尖刺附着在机身前面，可以显著改变流场，并在高超音速下操纵空气动力阻力。本文采用计算流体力学(CFD)方法，研究了不同长径比下平盘式气刺的实施效果。通过CFD分析，研究了安装气刺和不安装气刺时阻力、升力和俯仰力矩系数对钝体的影响。然而，在钝体前增加平盘气刺有利于减小迎角阻力，但必须考虑俯仰力矩的增加。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

2018 IEEE International Conference on System, Computation, Automation and Networking (ICSCA)

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