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基于动量定理的内阻测量误差大,常规高超声速通气模型测力试验精度无法满足应用需求。为此,提出了采用“尾支+六分量天平”直接测量作用在通气模型机体控制体上的待测气动特性的新型试验方法,并对相关理论基础、工作原理进行了讨论。借鉴大尺度通气模型内外流解耦设计经验完成了模型设计,在FD-20A风洞上开展了原理性试验,通过对比分析来验证新型试验方法。结果表明:基于相似理论和力分解原则的通气模型直接测力试验方法可行,测量数据准确可信;试验数据信息丰富,能够准确评判间隙密封效果;由于减少了内阻测量环节,通气模型直接测力试验精度高;当来流马赫数为6时阻力系数误差小于2%,远低于常规通气模型测力试验,满足应用需求。
The internal resistance measurement error based on the momentum theorem is large, and the precision of the conventional hypersonic ventilation model force measurement test can not meet the application requirements. For this reason, a new test method for measuring aerodynamic characteristics directly on the control body of the ventilation model using the “tail balance + six-component balance” is proposed. The relevant theoretical basis and working principle are discussed. Drawing on the experience of decoupling the inside and outside of the large-scale aeration model, the model design was completed. The principle test was carried out on the FD-20A wind tunnel and the new test method was verified through comparative analysis. The results show that the direct force test method based on the similarity theory and force decomposition principle is feasible and the measurement data is accurate and credible. The experimental data is rich in information and can accurately evaluate the gap sealing effect. Because of the reduction of internal resistance measurement, The force test accuracy is high. When the Mach number is 6, the drag coefficient error is less than 2%, much lower than that of the conventional venting model to meet the application requirements.