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Experimental investigation of the effects of leading edge bluntness on supersonic flow over a double compression ramp |
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| Authors: | Kim Ikhyun Park Gisu Byun Yung Hwan |
| Affiliation: | 1.Department of Aerospace Engineering, KAIST, Daejeon, 305-701, Korea ;2.Department of Engineering Science, The Southwell Building, University of Oxford, Oxford, OX2 0ES, UK ;3.Department of Aerospace Engineering, Konkuk University, Seoul, 14370, Korea ; |
| Abstract: | 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 13° and 40° 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. |
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