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- W2323094176 abstract "The angle of attack effect on the boundary layer transition of circular cone at hypersonic speed has been investigated by means of experimental study. A heat transfer rate measuring system has been developed based on very high frequency-responding thin film heat resistance sensors, with which the time-averaged mean value and fluctuation of heat flux on the wall of the experimental model can be obtained at the same time. Experiments have been performed in a piston gun tunnel at Mach number 6. The time averaged mean value and time dependent fluctuation of the heat transfer rate have been measured in the present study. The mean value of the heat transfer rate gives the boundary layer transition onset and peak position. The angle attack effect at small angle of attack agrees with previous researcher’s results well, that the boundary layer transition location on the windward of the cone moves backward and the transition location on the leeward of the cone moves forward when the angle of attack increases. Heat transfer rate fluctuation reveals that the turbulent structures are evident, but behave differently across the transition. Before the boundary layer transition, intermittent structure takes place in a low rate. In the boundary layer transition process, the intermittent structure occurrence increases in a high rate, and fluctuation amplitude of heat transfer rate reaches the highest value. After the boundary layer transition, the intermittent structure occurrence remains in a high rate, but the fluctuation amplitude of heat transfer rate decreases." @default.
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- W2323094176 date "2007-06-15" @default.
- W2323094176 modified "2023-10-17" @default.
- W2323094176 title "Measurement on Transition of Hypersonic Boundary Layer Over Circular Cone" @default.
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- W2323094176 doi "https://doi.org/10.2514/6.2007-6728" @default.
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