宽速域低声爆高效气动布局设计及风洞试验验证是新一代大超声速民机研究的难点和关键技术之一。首先，针对采用基于声爆最小化理论反设计方法、波系有益干扰后体设计方法以及参数化近场超压信号的混合可信度反设计方法提出的先进超声速民机低声爆气动布局，设计并加工了高速测力和声爆风洞试验模型；然后，根据声爆风洞试验耗气量大、流场品质要求高等特点，设计了无反射测压轨，发展了空间平均技术降低风洞背景流场非均匀扰动带来的测量误差，提高模型近场压力信号的测量精度；最后，针对所提出的超声速民机低声爆气动布局进行了声爆风洞试验测试和高速测力风洞试验测试，获得了高质量的声爆和测力风洞试验测量数据。研究表明：采用所述超声速民机低声爆气动布局设计及风洞试验方法可以获得较好的降声爆效果及较高的试验精度，具有较好的推广应用价值；高速测力和声爆试验测量结果与CFD计算结果一致性较好，验证了所发展的超声速民机低声爆气动布局设计及风洞试验验证方法的合理性。研究工作对超声速民机气动布局设计及风洞试验研究具有一定的工程指导价值。

Wide speed range low sonic boom high efficiency aerodynamic layout design and wind tunnel test method is one of the most important key technologies and difficulties for supersonic civil aircraft. First of all, used the methods of anti-design of sonic boom minimization theory and the aft-body design based on wave system beneficial interference and the mixed credibility anti-design method based on the parameterized near-field overpressure signal, an advanced low sonic boom supersonic civil aircraft aerodynamic layout is proposed in this paper, the high-speed force measurement and sonic boom wind tunnel test model are also designed and processed. Then, due to large gas consumption of sonic boom wind tunnel test and relatively high quality requirement of wind tunnel flow field, a non-reflective pressure gauge is designed and the spatial average technique is developed to reduce the measurement error caused by the non-uniform disturbance of the background flow field. Finally, the sonic boom and high-speed force wind tunnel test are carried out for the low sonic boom aerodynamic layout of the proposed supersonic civil aircraft, and the high-quality sonic boom and force test data are obtained.The results shows that use the proposed method for aerodynamic layout design and wind tunnel test of the supersonic civil aircraft can obtain better boom reduce effect and relatively high test precision, and have some application value for such aircraft design; The test results of high-speed force measurement and boom sonic test are in good agreement with those obtained by CFD method, and the rationality of the developed aerodynamic layout design and wind tunnel test method for supersonic civil aircraft is verified. The research work has certain engineering guiding values for aerodynamic layout design and wind tunnel test of supersonic civil aircraft.