Numerical Study on Aerodynamics Characteristics of R-HAN122 Along with Nose Modification

International Review of Aerospace Engineering Pub Date : 2023-06-30 DOI:10.15866/irease.v16i3.23400

James Julian, Waridho Iskandar, Fitri Wahyuni, Muhammad Ilham Adhynugraha, Fadilah Hasim

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Abstract

This study discusses the aerodynamics of the R-HAN 122 rocket and the modification of the nose shape using computational methods. Fluid flow simulation uses the RANS equation, which has been adjusted for compressible fluid flow. The turbulence model in this study is the standard k-ε. The analysis has been carried out in two dimensions. The mesh used is a structured mesh type using quadrilateral element shapes. The number of mesh elements used in this study is 2×105. The nose models in this study have been ogive (baseline), cone, and hemisphere. The fluid flow velocity in this study is Mach 1.602. The nose cone and the hemisphere shape can increase the Cl of the R-HAN 122 rocket at 4º

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R-HAN122机头改型气动特性数值研究

本文采用计算方法讨论了r - han122火箭的空气动力学特性和机头形状的改进。流体流动模拟使用RANS方程，该方程已针对可压缩流体流动进行了调整。本研究的湍流模型是标准的k-ε。分析是在两个维度上进行的。使用的网格是使用四边形元素形状的结构化网格类型。本研究中使用的网格单元数为2×105。本研究的鼻模型有半圆鼻(基线)、锥鼻和半圆鼻。本研究流体流动速度为1.602马赫。头锥和半球形可以使R-HAN 122火箭的Cl在4º<AoA<10º。然而，R-HAN 122 Cd型火箭在机头形状被修改为锥形或半球形时增加。基线r - han122和锥形鼻头的最佳AoA为6º。将R-HAN - 122型头火箭改型为半球形后，可获得8°的最佳AoA。激波在r - han122周围形成，改变了激波区的密度和马赫数。锥形鼻子承受的压力最小，而半球形鼻子承受的压力最大。

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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International Review of Aerospace Engineering

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