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거칠기 천이 모델을 이용한 초음속 이중 원추 선두부의 열전달 해석
신호철(H.C. Shin),박수형(S.H. Park) 한국전산유체공학회 2020 한국전산유체공학회지 Vol.25 No.4
Laminar to turbulent boundary layer transitions cause increased drag and heat transfer of a vehicle. One of the main causes of the laminar to turbulent boundary layer transition is the transition due to surface roughness, but it is generally not considered. However, in the case of a hypersonic or re-entry vehicle, The high speed and temperature of vehicle result in inadvertent surface roughness. In addition, surface roughness is intentionally used to avoid separation and instability of the boundary layer. This study presents an hypersonic transition model to analyze the laminar to turbulent boundary layer transition due to surface roughness. Computational results were validated by comparing them with the experiment of a subsonic and hypersonic flat plate. The hypersonic biconic nose tip with surface roughness was analyzed using the verified hypersonic transition model, and the change of the transition point and the increase in heat transfer due to the surface roughness were investigated.