Influence of Quiet Spike on Supersonic Transport for Low Boom Effect

静音锥对超声速民机低声爆效果的影响

School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China

Received: 1 March 2018

Abstract

One of the biggest technical challenges of supersonic flight is the mitigation of sonic boom. To deal with this problem, the Gulfstream Aerospace Corporation came up with the spike concept, and it showed to be efficient. However, there also remain several problems, the first one is that installing the spike makes it harder to balance for supersonic transport and the another one is that the movement equipment is complex. In this paper, a new concept by replacing the multi-stage of the normal spike with smooth transistion cones is proposed. The concept simultaneously uses the CFD solver HUNS3D based on the Reynolds average (RANS) equation and the far-field FL-BOOM sound explosion propagation program based on Thomas waveform parameter method. The effectiveness of the present scheme to suppress supersonic aircraft sound explosion is verified according to the concept. It is proved that the increased length is good for low blast and the main factor affecting the blast reduction effect of multistage mute cone is length rather than series by the analysis. The results have important reference value for the silent cone design of supersonic aircraft.

摘要

声爆问题是制约超声速客机商业运营的重要因素之一。为抑制声爆，湾流公司提出了安装于机头的静音锥方案，取得了一定的效果。但静音锥方案也存在一定的不足，主要体现在难以配平以及作动机构复杂的问题。针对此问题提出了一种改进的圆滑过渡静音锥方案，并使用基于雷诺平均（RANS）方程的CFD求解器HUNS3D和基于Thomas波形参数法的远场FL-BOOM声爆传播程序，验证了所提方案对于抑制超声速飞机声爆的有效性，并就静音锥的多项特征对其降低声爆效果的机理进行了分析，证明了影响多级静音锥降爆效果的主要因素是长度而不是级数，但长度增加对低声爆效果也有利。研究结果对超声速飞机静音锥设计具有重要的参考价值。