Results of a physical experiment aimed at measuring the profile of relative excess pressure on a control surface in the near zone of the disturbed region of a schematized model of supersonic passenger aircraft (SPA) are reported. Tests in the test section of the T-313 wind tunnel, aimed at identification of the optimum mounting of SPA-model suspension and ensuring measurements of the full profile of the disturbed-pressure wave involving the leading, intermediate, and closing shock waves, were carried out. Comparisons of calculated data with experimental results are presented. Using the revealed optimum model suspension, measurement results in good agreement with the results of numerical calculations are obtained. The numerical solution to the problem about the flow around the geometric model was obtained and the necessary measurements in the experiment were carried out at freestream Mach number M_∞ = 2.04 and angle of attack α = 4°.

中文翻译：

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SPA型悬架总成对离源固定距离处测得的过压曲线的影响

报告了旨在测量超音速客机（SPA）模式化模型的受扰区域附近区域中控制面上相对过大压力分布的物理实验结果。在T-313风洞的测试部分进行了测试，旨在确定SPA型悬架的最佳安装方式，并确保测量涉及前，中和闭合冲击波的压力波的完整轮廓。执行。给出了计算数据与实验结果的比较。使用揭示的最佳模型悬架，可以获得与数值计算结果非常吻合的测量结果。_∞ = 2.04，迎角α = 4°。