Flight tests and predictions of sonic boom signature for supersonic aircraft

QU Lixia; HAN Shuo; SONG Yahui; XU Yue; ZHANG Yuelin

doi:10.7638/kqdlxxb-2022.0018

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Flight tests and predictions of sonic boom signature for supersonic aircraft

更新时间：2026-05-28

- Flight tests and predictions of sonic boom signature for supersonic aircraft
- Vol. 40, Issue 4, Pages: 69-80(2022)
- 作者机构：
  
  1. 中国航空研究院,北京,100012
  2. 中国飞行试验研究院,西安,710089
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2022.0018
  CLC： TB533+.3;V217+.3
- Published：2022
- 稿件说明：
移动端阅览
瞿丽霞, 韩硕, 宋亚辉, 等. 超声速飞行器声爆飞行试验与声爆预测评估[J]. 空气动力学学报, 2022, 40(4): 69−80.

QU Lixia, HAN Shuo, SONG Yahui, et al. Flight tests and predictions of sonic boom signature for supersonic aircraft[J]. 2022, 40(4): 69-80.
瞿丽霞, 韩硕, 宋亚辉, 等. 超声速飞行器声爆飞行试验与声爆预测评估[J]. 空气动力学学报, 2022, 40(4): 69−80. DOI： 10.7638/kqdlxxb-2022.0018

QU Lixia, HAN Shuo, SONG Yahui, et al. Flight tests and predictions of sonic boom signature for supersonic aircraft[J]. 2022, 40(4): 69-80. DOI： 10.7638/kqdlxxb-2022.0018.

摘要

声爆问题是超声速民机研制中首要解决的关键问题之一。声爆飞行试验是研究超声速飞行器声爆特性的最直接手段，可为声爆预测方法和低声爆设计技术提供真实可信的验证数据，对新一代低声爆超声速民机设计具有重要意义。中国航空研究院与中国飞行试验研究院发展了基于传感器阵列的地空一体化地面声爆测量技术，开展了国内首次超声速飞机声爆专项测试飞行试验，采集了多组真实大气条件下的声爆实测数据，验证了飞行试验方案的合理性。在飞行航迹正下方测得的声爆波形具有显著相关性，声爆信号头激波峰值相对误差在18%左右，尾激波峰值相对误差在8%左右，声爆持续时间均为0.1 s。对比分析了地面声爆实测数据与数值预测结果，发现：飞行器从测量阵列正上方飞过时，得到的声爆信号基本形态一致、持续时间较接近，声爆信号头激波、机翼前缘激波峰值相对误差小于5%；由于计算模型简化和声爆长距离传播的非线性累积效应等因素，导致声爆信号预测值与实测值在局部特征上有一定差异；后续还需深入研究真实大气环境下的超声速声爆远场传播预测方法。

Abstract

The problem of sonic boom is one of key problems to be solved in the development of supersonic civil aircraft. In-flight flow-field signature measurements is the most direct method to study the sonic boom characteristics of supersonic aircraft. It can provide truly credible verification data for the sonic boom prediction method and low sonic boom design technology

which is of great significance to the design of a new generation of low-sonic boom supersonic civil aircraft. Technologies related to sonic boom flight test track planning

ground-air integrated large-scale array sonic boom measurement are developed by Chinese Aeronautical Establishment and Chinese Flight Test Establishment. The first domestic special in-flight sonic boom test program of supersonic aircraft was carried out

collecting multiple sets of sonic boom measured data under real atmospheric conditions

which confirmed the rationality of the in-flight test plan. The sonic boom waveform measured on track has significant correlation. The relative error of the sonic boom signal bow shock peak is about 18%

which of the tail shock peak is about 8%. The duration of the sonic boom signature is around 0.1 s. The far-field boom measured data and numerical prediction results are compared and analyzed. When the aircraft flies over the measurement array

the basic shape of the sonic boom signatures obtained is consistent

and the duration is relatively close. The relative error between the peak values of the bow shock and the wing leading edge shock is less than 5%. However

due to factors such as the simplification of the simulation model and the nonlinear cumulative effect of the long-distance propagation of the sonic boom

the predicted sonic boom signals have certain differences in local characteristics

which requires further research on the prediction method of far-field sonic-boom in real atmospheric environment.

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references

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