Experimental investigation of the effects of leading edge bluntness on supersonic flow over a double compression ramp

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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 degrees and 40 degrees 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.
Publisher
KOREAN SOC MECHANICAL ENGINEERS
Issue Date
2020-10
Language
English
Article Type
Article
Citation

JOURNAL OF MECHANICAL SCIENCE AND TECHNOLOGY, v.34, no.10, pp.4193 - 4199

ISSN
1738-494X
DOI
10.1007/s12206-020-0911-z
URI
http://hdl.handle.net/10203/277185
Appears in Collection
AE-Journal Papers(저널논문)
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