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http://dx.doi.org/10.5139/JKSAS.2012.40.12.1025

Study on Concept Design of Supersonic Inlet and Flow Control of Bleeding under Operating Condition  

Choi, Jaehwan (Department of Mechanical and Aerospace Engineering, Seoul National University)
Cheon, Somin (Department of Mechanical and Aerospace Engineering, Seoul National University)
Choe, Yohan (Department of Mechanical and Aerospace Engineering, Seoul National University)
Hong, Wooram (Interdisciplinary Program in Computational Science and Technology, Seoul National University)
Kim, Chongam (Department of Mechanical and Aerospace Engineering, Seoul National University)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.40, no.12, 2012 , pp. 1025-1031 More about this Journal
Abstract
The present paper deals with concept design of supersonic inlet based on compressible flow theory and flow control of bleeding in order to guarantee stability of supersonic inlet of ramjet engine in broad range of operating conditions. Shock instability, shock wave-boundary layer interaction and flow separation should be properly controlled to improve performance of the supersonic inlet. Considering shock strength, boundary layer and flow separation, the supersonic inlet is modified from the basic model which is designed under inviscid theory. Consequently, shock is stabilized, and required mass flow rate is obtained. Furthermore, bleeding is applied to the supersonic inlet to maintain performance in off-design conditions. Mass flow condition is adopted for modeling of bleeding effect, and performance of the supersonic inlet is evaluated by changing bleeding locations and numbers.
Keywords
Supersonic Inlet; Bleeding; Shock Wave-Boundary Layer Interaction; EDISON_CFD;
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