| 静音锥对超声速客机声爆水平的影响 |
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| 引用本文： | 李占科,彭中良,徐合良.静音锥对超声速客机声爆水平的影响[J].航空工程进展,2013,4(3):346-351,357. |
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| 作者姓名： | 李占科 彭中良 徐合良 |
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| 作者单位： | 西北工业大学航空学院,西安,710072 |
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| 摘 要： | 静音锥低声爆是通过在超声速飞机头部加装静音锥将机头产生的强激波转化为一系列互不叠加的弱激波，从而降低声爆。以一种“梭式”布局的超声速客机为基本模型，采用计算流体力学和波形参数法相结合的方法，研究不同参数的单级和多级静音锥对超声速客机声爆水平的影响。结果表明：静音锥的长度可以调节激波的干涉程度；静音锥的直径和圆锥顶角可以改变静音锥的初始超压值；静音锥级数对上升时间影响显著。
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| 关 键 词： | 超声速客机 激波 声爆 静音锥 计算流体力学 |
Effect of the Quiet Spike on Sonic Boom of the Supersonic Airliner |
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| Li Zhanke
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Peng Zhongliang
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Xu Heliang.Effect of the Quiet Spike on Sonic Boom of the Supersonic Airliner[J].Advances in Aeronautical Science and Engineering,2013,4(3):346-351,357. |
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| Authors: | Li Zhanke Peng Zhongliang Xu Heliang |
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| Affiliation: | (School of Aeronautics, Northwestern Polytechnical University, Xi＇ an 710072, China) |
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| Abstract: | The Quiet Spike is a telescoping forward fuselage extension that alters the bow shock of the classic N- wave pressure signature generated by aircraft travelling at supersonic speed. The how shock is broken up into sequence of weak shocks to reduce sonic boom. Supersonic airliner of the ＂shuttle＂ layout is analyzed. Based on CFD（Computerized Fluid Dynamics） and waveform parameter method, different geometrical parameters of multi-segment quiet spikes are studied. The results shows that length of quiet spike can regulate the interference degree of the shock wave, diameter and vertex angle can decide the initial pressure of the quiet spike,the seg- ment makes a significant influence on the rising time. |
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| Keywords: | supersonic airliner shock wave sonic boom quiet spike CFD |
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