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http://dx.doi.org/10.5139/JKSAS.2017.45.5.367

Transition Flow Analysis According to the Change of Reynolds Number for Supersonic Launch Vehicle Fairing Expansion Area  

Shin, Ho-Cheol (Department of Aerospace Engineering, Konkuk University)
Park, Soo-Hyung (Department of Aerospace Engineering, Konkuk University)
Byun, Yung-Hwan (Department of Aerospace Engineering, Konkuk University)
Publication Information
Journal of the Korean Society for Aeronautical & Space Sciences / v.45, no.5, 2017 , pp. 367-375 More about this Journal
Abstract
RANS computational analysis was performed on the head of the launch vehicle including the hammerhead nose pairing in the supersonic regime. The two-dimensional axisymmetric analysis was performed by using laminar, fully turbulent and transition models and compared with the experimental data. It was observed that different flow phenomena occurred depending on the Reynolds number. Under the high Reynolds number condition, the boundary layer becomes turbulent, which is not separated from the surface of the launch vehicle. With the low Reynolds number condition, laminar separation bubble was produced due to the separation and reattachment of the boundary layer on the expansion-compression edge of the hammerhead type nose fairing. The three-dimensional computations with the angle of attack showed a fully detached vortical structure due to the laminar separation bubble. It is proved that the turbulent transition should be considered to predict the separation bubble with the Reynolds number.
Keywords
Launch Vehicle; CFD; Supersonic Flow; Boundary Layer; Flow Transition;
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