Experimental Characterization of the Supersonic Transitional Wake Downstream of a Single Roughness Element  

作　　者：BOTTINI Henny SARACOGLU Bayindir H. PANIAGUA Guillermo 

机构地区：[1]Department of Aerospace Engineering,Nagoya University,Nagoya 464-8603,Japan [2]Aeronautics and Aerospace Department,von Karman Institute for Fluid Dynamics,Rhode-Saint-Genese B-1640,Belgium [3]Zucrow Laboratories,Purdue University,500 Allison Road,West Lafayette 47907,IN,USA

出　　处：《Journal of Thermal Science》2020年第4期1085-1093,共9页热科学学报（英文版）

摘　　要：An experimental campaign was carried out to investigate the characteristics of the transitional supersonic wake downstream of a single roughness element. Two Mach numbers were tested, 1.6 and 2.3, and two roughness heights, 0.1 mm and 1 mm. Unsteady and steady wall temperature measurements were taken along and across the roughness wake. The spatial trends of adiabatic wall temperature and heat flux, and the spectral time evolution of temperature were documented in this paper. The initial wall temperature was varied during the temperature measurements, and the resulting steady and unsteady effects on the roughness wake were investigated. The streamwise trends of heat-flux and adiabatic-wall temperature confirmed the transitional nature of the roughness wake. Spectral analysis showed that roughness height and initial wall temperature had the same type of effect on the wake wall-temperature fluctuations. The effect of roughness height was more sensible at Mach 2.3, and that of the initial wall temperature was more evident with the smallest roughness also tested at Mach 2.3.

关 键 词：supersonic boundary layer roughness wake steady measurements unsteady measurements heat transfer 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]