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Lateral cutoff analysis of sonic boom using full-field simulation

机译：使用全场模拟对声波臂进行横向截止分析

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This paper describes the world's first successful simulation for lateral cutoff phenomena of sonic boom far from the flight path due to variation in atmospheric temperature with altitude. A flow field around an axi-symmetric paraboloid has been analyzed by the full-field simulation method that solves the three-dimensional Euler equations with a gravity term to create a horizontally stratified atmosphere. A solution-adapted structured grid is constructed to align the grid lines with the front and rear shock-wave surfaces in the entire domain, including the near field around a supersonic body and far field reaching the ground beyond lateral cutoff. The flight is assumed to have a speed of Mach 1.2 at an altitude of 10 km, and the computational domain ranges over a distance of 30 km from the axis of symmetry. The computational results show that the evanescent wave in the shadow zone beyond lateral cutoff decays exponentially and changes into a progressive rounding waveform. The characteristics of the waveform transition are in good agreement with those observed in the flight tests. Therefore, the full-field simulation is recognized as a promising approach for investigating sonic boom strength in the full extent of sonic boom noise, including lateral cutoff and evanescent waves. Moreover, the computational results clarify that sonic boom focusing occurs above the ground, except for the vicinity of the ground, and the focusing strength along the lateral cutoff curve detected from the three-dimensional shock-wave surface increases with altitude. The results of ray tracing analysis collaborate the reasonability of the simulation results, and the caustic of downward convex agrees well with the lateral cutoff curve. In the shadow zone, the magnitude of exponential decay increases with altitude, and the lateral distance where the pressure rise decreases rapidly shortens with altitude. (C) 2019 Elsevier Masson SAS. All rights reserved.
机译：本文描述了世界上第一个成功模拟的，由于大气温度随高度变化而导致的，远离飞行路径的音爆的横向截止现象。已经通过全场模拟方法分析了轴对称抛物面周围的流场，该方法用重力项求解三维欧拉方程，从而产生水平分层的大气。构造了一种适用于解决方案的结构化网格，以使网格线与整个范围内的前后冲击波表面对齐，包括超音速体周围的近场和到达横向截止之外的地面的远场。假设该飞行器在10 km的高度处的速度为1.2马赫，其计算域在距对称轴30 km的范围内。计算结果表明，超出侧向截止的阴影区域中的van逝波呈指数衰减，并变为渐进的舍入波形。波形过渡的特性与飞行测试中观察到的特性非常吻合。因此，全场模拟被认为是一种在包括横向截止和van逝波在内的整个声波噪声中研究声波强度的有前途的方法。而且，计算结果表明，除了地面附近以外，声波悬臂聚焦发生在地面以上，并且从三维激波表面检测到的沿横向截止曲线的聚焦强度随高度而增加。射线追踪分析的结果与模拟结果的合理性相吻合，并且向下凸的苛性与横向截止曲线非常吻合。在阴影区，指数衰减的幅度随着高度的增加而增加，而压力上升迅速减小的横向距离则随着高度的增加而缩短。 （C）2019 Elsevier Masson SAS。版权所有。

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