Experimental investigation of the effects of leading edge bluntness on supersonic flow over a double compression ramp
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DOI 10.1007/s12206-020-0911-z
Journal of Mechanical Science and Technology 34 (10) 2020 Original Article DOI 10.1007/s12206-020-0911-z Keywords: · Double compression ramp · Bluntness leading edge · Supersonic flow · Flow visualization · Wind tunnel experiment
Correspondence to: Ikhyun Kim [email protected]
Experimental investigation of the effects of leading edge bluntness on supersonic flow over a double compression ramp Ikhyun Kim1,2, Gisu Park1 and Yung Hwan Byun3 1
2
Department of Aerospace Engineering, KAIST, Daejeon 305-701, Korea, Department of Engineering 3 Science, The Southwell Building, University of Oxford, Oxford OX2 0ES, United Kingdom, Department of Aerospace Engineering, Konkuk University, Seoul 14370, Korea
Abstract Citation: Kim, I., Park, G., Byun, Y. H. (2020). Experimental investigation of the effects of leading edge bluntness on supersonic flow over a double compression ramp. Journal of Mechanical Science and Technology 34 (10) (2020) 4193~4199. http://doi.org/10.1007/s12206-020-0911-z
Received May 4th, 2020 Revised
August 7th, 2020
Accepted August 10th, 2020 † Recommended by Editor Yang Na
© The Korean Society of Mechanical Engineers and Springer-Verlag GmbH Germany, part of Springer Nature 2020
Understanding the flow characteristics over a double compression ramp is crucial for high-speed vehicle design. Leading edge bluntness is a key factor influencing the formation of a separation region on a double compression ramp flow. In the present study, the effect of bluntness on a double compression ramp is investigated experimentally at a nominal Mach number of 4. The test model has 13º and 40º inclinations with respect to the freestream. Five different levels of leading-edge radius, varying from 0.0 to 2.0 mm, were subjected to supersonic wind tunnel tests. Shadowgraph and infrared thermography techniques were employed to visualize the flow features of the double ramp model. Measurements of surface heat-transfer along the centerline of the test model were obtained from the acquired infrared images. It is shown that the leading-edge radius alters the separation characteristics as well as the surface heat-transfer. Possible reasons for such flow characteristics are discussed.
1. Introduction The compression ramp, one of the most fundamental geometries, is considered in the design of high-speed vehicles. It is known that the flow field of a compression surface is dominated by shock wave/boundary layer interactions that induce extended separations and cause boundary layer instability, and high thermal pressure loads on the surface [1-3]. During supersonic flights, such interactions are likely to be important factors that affect the vehicle performance. Hence, control mechanisms for this flow feature have been the subject of many investigations. Some studies have reported mechanisms for controlling the separation size of the compression ramp. Understanding the separation characteristics induced by shock wave/boundary layer interactions is crucial for high-speed vehicle engineering and imp
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