宽体客机高速风洞试验数据修正方法

宽体客机航程远、巡航马赫数高，其气动设计对风洞试验数据精准度要求很高。通过完善中国空气动力研究与发展中心FL-26风洞试验数据修正技术和设备，对宽体客机高速风洞测力试验数据进行支撑/洞壁干扰、模型变形及流场畸变等系统修正，获取干净、可靠的风洞试验基准数据，为开展雷诺数、静气动弹性和动力影响等相关性修正奠定基础。研究表明：支撑干扰试验时，尾腔压力分布测量位置和假支杆长度伸入模型尾腔50 mm即可获得可靠的支撑干扰试验结果；在试验包线范围内，洞壁干扰对宽体客机模型升力、阻力和俯仰力矩系数影响较小；试验模型变形对宽体客机气动特性影响较为明显，马赫数0.85时模型变形后的升力线斜率减小0.005左右，焦点前移0.021 b_A，需进行相关修正。

Method of test data correction for wide-body aircraft in high speed wind tunnel

Due to its long range and high cruise Mach number, the aerodynamic design of wide-body aircraft requires high precision of its wind tunnel data. To obtain reliable base data of wind tunnel for wide-body aircraft, this paper improves the correction method and related facility in FL-26 wind tunnel of China Aerodynamics Research and Development Center. The test data of high-speed wind tunnel for wide-body aircraft are corrected in several ways, including boundary constrains (support and wall interference), model deformation and flow distortion (flow angle and buoyancy drag). These corrections lay a firm foundation for Reynolds numbers, hydroaeroelasticity and dynamic effect. Results indicate that reliable test results of supporting interference can be obtained by measuring the distribution of the positions of the tail cavity pressure and the length of the false support rod extending into the tail cavity of the model by 50 mm. Within the range of the test envelope, the wall interference has minor influence on the lift, drag and pitch moment coefficients of the wide-body aircraft model. The deformation of the test model significantly influences the aerodynamic characteristics of the wide-body aircraft. After deformation, the lift slope at Mach number=0.85 decreases by 0.005, and the moment focus is moved forward by 0.021 b_A. These discrepancies need to be corrected in future tests.