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您的检索式：作者名="Linxuan ZUO"
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| 1 | Effects of flexibility on aerodynamic performance of delta wings with different sweep angles显示文摘Force measurement and surface oil flow visualization experiments were conducted in a wind tunnel to investigate the effects of flexibility on aerodynamic performance of delta wings with different sweep angles.The experimental results indicate that the maximum lift coefficient is increased and the stall angle is delayed as the sweep angle increases for both rigid and flexible wings.It is also found that the maximum lift coefficients of the flexible wings with a sweep angle from 35° to 50° are higher than those of the rigid ones.The increment of the maximum lift coefficient in particular achieves 32.9% compared with the case without lift enhancement for the 40° flexible delta wing.Moreover,the surface oil flow visualization experiments show that the stall of the flexible wing of the moderate low sweep angle is accompanied by helical flow structure,while the vortex bursting appears on the corresponding rigid wing. | LIU Yang,ZUO LinXuan & WANG JinJun Institute of Fluid Mechanics,Beijing University of Aeronautics and Astronautics and Fluid Mechanics Key Laboratory,Ministry of Education,Beijing 100191,China | 2010 | Science China(Physics,Mechanics & Astronomy)2010，53，5： | 2 |
| 2 | Preliminary study on heat flux measurement data of TT-0 flight test显示文摘With the explosive development of aerospace science,the design of the new generation airliner at higher speeds is attracting more attentions.To achieve this goal,it is necessary to achieve accurate prediction of the aerodynamic heating/force loads and successful reduction of drag and heat flux.As a remedy for the existing studies which are based upon the CFD and wind tunnel tests,this study presents a flight test for the drag and heat reduction spike technology.The principal goals of this flight test were to provide reference for verifying the accuracy of the prediction technology on ground and promote the development of the drag and heat reduction technology.By adopting the OS-X rocket,the TT-0 test vehicle designed by Shenyang Aircraft Design&Research Institute reached a maximum Mach number of 5.8 and a maximum altitude of 38 km.Hypersonic and supersonic pressure data by pressure scanning valves and heat fluxes by gauges at different locations were obtained successfully.Also,heat fluxes obtained by in-house CFD code are illustrated in comparison with the flight data.The results indicate that the numerical errors are large in most cases.More technologies,such as more CFD codes and more numerical procedures,should be adopted to conduct studies on this issue in the future. | Enwei LU Linxuan ZUO Zheng GUO Honggang ZENG Wei ZHU Feng QU | 2021 | Chinese Journal of Aeronautics2021，34，5： | 0 |
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