2.4m跨声速风洞压敏漆测量系统研制与应用研究

发布时间：2018-03-20 10:29

本文选题：跨声速风洞　切入点：压敏漆技术　出处：《实验流体力学》2016年03期 　论文类型：期刊论文

【摘要】：近十几年来,由于压敏漆(Pressure Sensitive Paint、PSP)测量技术的不断完善与发展,国际上主要空气动力试验机构逐步将其应用于2m量级工程型风洞,完成模型表面压力测量、模型表面流动显示与CFD结果验证。在2.4m跨声速风洞建立了双组份、多光源和多CCD的PSP测量系统,解决了大型暂冲式跨超声速风洞试验存在的模型表面温度变化、光照均匀性与强度变化,以及模型振动、试验数据修正、喷涂与压敏涂料校准等诸多影响PSP测量结果精准度与可靠性的问题,并成功应用于大飞机测压模型和三角翼测压模型压力分布测量试验。试验结果表明:在小迎角范围压敏漆涂层对模型表面压力分布影响不明显;在试验马赫数0.4~0.82、模型迎角-4°~4°范围,PSP与传统电子扫描阀测量结果的Cp均方根偏差小于0.03,测量精准度与国外同量级连续式跨声速风洞相当。可以为飞行器气动优化设计和空气动力学研究提供一种新的、先进的测试技术。
[Abstract]:In the past ten years, due to the continuous improvement and development of pressure Sensitive PSPs measurement technology, the main aerodynamic testing institutions in the world have gradually applied it to engineering wind tunnels of 2m magnitude to measure the surface pressure of the model. A two-component, multi-light source and multi-#en1# PSP measurement system was established in 2.4m transonic wind tunnel to solve the model surface temperature change in large-scale transonic wind tunnel test. The variation of illumination uniformity and strength, the vibration of model, the correction of test data, the calibration of spraying and pressure-sensitive coating, etc., which affect the accuracy and reliability of PSP measurement results. It has been successfully applied to the pressure distribution measurement of large aircraft and delta wing pressure measurement models. The experimental results show that the pressure distribution of the model surface is not significantly affected by the pressure-sensitive paint coating in the range of small angle of attack. At the test Mach number of 0.4m 0.82, the mean square deviation of CP between PSP and traditional electronic scanning valve is less than 0.03 in the range of model angle of attack -4 掳and 4 掳. The accuracy of measurement is equivalent to that of the continuous transonic wind tunnel of the same order in foreign countries. It can be designed for aerodynamic optimization of aircraft. And aerodynamics research provides a new kind of. Advanced testing techniques.
【作者单位】：中国空气动力研究与发展中心;
【分类号】：V211.74

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