Unsteady Pressure Measurement of Transonic Buffet on NASA Common Research Model
Unsteady Pressure Measurement of Transonic Buffet on NASA Common Research Model
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NASA 通用研究模型上跨音速抖振的非定常压力测量
DOI：
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发表时间：
2016
期刊：
影响因子：
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通讯作者：
A. Hashimoto
中科院分区：
文献类型：
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作者：
S. Koike;M. Ueno;K. Nakakita;A. Hashimoto
为了获得非定常计算流体力学的验证数据，弄清NASA一个缩比为80%的通用研究模型的抖振现象，在JAXA 2m×2m跨音速风洞中进行了跨音速抖振实验研究。在跨音速抖振条件下，成功地测量了主翼两条流线上的非定常压力分布。均匀流的马赫数为0.85。基于参考弦长的雷诺数分别为1.515×10和0.947×10。机翼上的激波振荡可分为三个区域，即无分离的小振荡区、功率谱上有凸起的振荡区和功率谱上有宽带的大振荡区。基于碰撞峰值频率的Strouhal数约为0.3。互相关分析和相位分析表明，撞击频率的压力脉动从翼根侧向翼尖侧传播。
Experimental investigation of transonic buffet was conducted in JAXA 2m×2m transonic wind tunnel in order to obtain the validation data for unsteady computational fluid dynamics and to clarify the buffet phenomena of an 80% scaled NASA common research model. Unsteady pressure distributions on the two lines of the main wing were successfully measured on the transonic buffet condition. Mach number of the uniform flow was 0.85. Reynolds numbers based on the reference chord length were 1.515×10 and 0.947×10. The shockwave oscillation on the wing can be classified into three regions, a small oscillation region without separation, an oscillation region with bump in the power spectrum, and a large oscillation region with broadband power spectrum. The Strouhal number based on the bump peak frequency was about 0.3. The cross-correlation and the phase analysis revealed that the pressure fluctuation of the bump frequency propagated from the wing root side to the wing tip side.