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Wei F.,Air Breathing Hypersonic Technology Research Center | He X.-Z.,Air Breathing Hypersonic Technology Research Center | He X.-Z.,China Aerodynamics Research And Development Center | He Y.-Y.,Air Breathing Hypersonic Technology Research Center | And 2 more authors.
Tuijin Jishu/Journal of Propulsion Technology | Year: 2015

A new design thought of inner cone flow-field for inward turning inlet is presented. The basic flow-field is designed by rotational method of characteristics, including two shock waves, the leading edge shock wave and the ending shock wave. There is no continuous shock reflection along the internal flow-path. The numerical simulation results show that, the incident locations of the two shock waves are in full compliance with the design and there is no shock reflection at inlet shoulder. And that the distribution of Mach Number along the ramp obtained by the rotational method of characteristics agrees well with the CFD results. The flow parameter at throat is almost uniform and the total pressure recovery coefficient is 0.91. The stream-traced inlet totally inherits the basic flow-field characteristics at inviscid condition. Flow capture coefficient is 0.999. Total pressure recovery coefficient is 0.88, which is almost equal to the value of stream-traced Busemann inlet at the same design condition. ©, 2015, Editorial Department of Journal of Propulsion Technology. All right reserved. Source


He X.,Air Breathing Hypersonic Technology Research Center | He X.,China Aerodynamics Research And Development Center | Ni H.,Air Breathing Hypersonic Technology Research Center | Ni H.,China Aerodynamics Research And Development Center
Lixue Xuebao/Chinese Journal of Theoretical and Applied Mechanics | Year: 2011

The osculating curved cone (OCC) waverider design methods are put forward in the present paper. The flow field structure and aerodynamic characteristics of OCC waverider are also analysed. The OCC waverider uses curved cone as basic osculating flow field in which has straight shock wave and isentropic compression wave structures. The osculating axisymmetric and streamline tracing techniques are used to generate the OCC waverider when defining the inlet capture curve (ICC) and front capture tube (FCT). Computational fluid dynamic (CFD) methods are used to simulate the designed OCC waverider. Theoretical design results agree well with numerical simulating results. The comparisons are also made between osculating cone (OC) waverider and OCC waverider. It is show that OCC waverider overcomes the disadvantages of low compression abilities and small volumetric capabilities which OC waverider has. Source


He X.-Z.,China Aerodynamics Research And Development Center | He X.-Z.,Air Breathing Hypersonic Technology Research Center | Qin S.,Air Breathing Hypersonic Technology Research Center | Zeng X.-J.,China Aerodynamics Research And Development Center | And 2 more authors.
Tuijin Jishu/Journal of Propulsion Technology | Year: 2014

The accurate simulation of afterbody nozzle plume interference is not only very important to predict the aerodynamic force of the large scale integrated vehicle, but also crucial to understand the mechanisms of the afterbody nozzle plume interference. Researches about the experiment scheme of plume interfere have been carried out based on similarity theory. The simulation of specific heat ratio of the hot plume of the scramjet outlet has been put forward by using the mixture gases of CF4 and air. The numerical simulation and validation have been accomplished for the afterbody flow disturbance problem of air-breathing hypersonic vehicle. By using numerical simulation software, numerical modeling for afterbody nozzle plume interference have been studied under flight condition and wind tunnel condition. According to the result of numerical simulation, this afterbody nozzle plume interference experiment scheme for the outflow of similar parameter in simulation is feasible. Source


Xuzhao H.,China Aerodynamics Research And Development Center | Xuzhao H.,Air Breathing Hypersonic Technology Research Center | Jialing L.,China Aerodynamics Research And Development Center | Jialing L.,Air Breathing Hypersonic Technology Research Center | And 6 more authors.
18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012 | Year: 2012

The Osculating Inward turning Cone Waverider Inlet (OICWI) integrated design methods are put forward in present paper. The performance of an OICWI is analyzed using CFD software. Wind tunnel experiment is conducted for the OICWI. The design methods of OICWI use stream line tracing method and Osculating Inward turning cone methods. The design methods are according with aerodynamic principle and the waverider forebody inlet is integrated designed. The inviscid numerical simulation results are compared well with theoretical design results on design condition. The design and off design condition viscous numerical simulation results show that OICWI has high pressure recovery. It's isolate exit flow field has good uniformity. OICWI has high flow capture ratio and small amount of flow spillage. The experimental results show that the OICWI can successfully start from Mach number 5 to Mach number 7, the flow field structure and pressure distributions are compared well with numerical analysis results. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Source

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