论文部分内容阅读
针对等弦长带后掠半模SCCH增升构型襟翼附面层发生流动分离,线性段增升效率降低的问题,采用数值模拟和风洞试验方法,开展微型涡流发生器控制襟翼附面层流动分离研究.首先,采用数值方法分析SCCH增升构型的基本流动现象,获得襟翼流动分离特性,作为微型涡流发生器设计依据;其次,根据涡流发生器工作原理,结合SCCH增升构型襟翼结构与流动分离特性,提出本文微型涡流发生器设计思想和初步设计方案;再次,采用数值方法研究微型涡流发生器控制增升装置流动分离的作用机理,研究微型涡流发生器布置方式、弦向位置、安装角、高度、展向间距等几何参数对流动控制效能的影响规律,提出控制襟翼流动分离的微型涡流发生器设计方案,供风洞试验验证;完成数值设计之后,采用风洞试验方法,进行微型涡流发生器设计方案验证与可能的方案筛选,以验证数值模拟方法、设计方法及涡流发生器设计方案;最后,分析数值模拟和风洞试验研究结果,提出具有工程应用价值的增升装置微型涡流发生器设计原则、设计方法及技术路线,供型号研制借鉴与采纳.研究结果表明,本文针对SCCH着陆构型提出的微型涡流发生器设计方案,经CFD和风洞试验验证,在着陆及下滑进场飞行状态,最大增升与增阻量分别达到10%和14%,符合着陆飞行状态对增升装置的设计要求,且CFD方法提出的设计方案最佳,具有惟一性;同时也表明,本文提出的增升装置微型涡流发生器设计原则、设计方法及技术路线可用于型号研制.
Aiming at the problem that flow separation and linear increasing efficiency of flaps in the SCCH incremental structure with the same chord length are swept, the numerical simulation and the wind tunnel test method are used to carry out the micro vortex generator control flaps’ First of all, the basic flow phenomenon of SCCH rising configuration is analyzed by numerical method, and the flap flow separation characteristic is obtained, which is used as the design basis of micro vortex generator. Secondly, according to the working principle of vortex generator and SCCH increasing configuration Flap structure and flow separation characteristics of the proposed micro-vortex generator design ideas and preliminary design; Third, the use of numerical methods to study the micro-vortex generator flow control devices to enhance the separation mechanism, the micro-vortex generator arrangement, the string The design scheme of micro-vortex generator which controls the flow separation of the flap is put forward for the test of the wind tunnel. After the numerical design is completed, the design of the micro-vortex generator with the wind tunnel Test method, micro vortex generator design verification and possible screening programs to verify the numerical simulation Method, design method and vortex generator design. Finally, the numerical simulation and wind tunnel test results are analyzed, and the design principle, design method and technical route of micro-vortex generator for lifting device are put forward for reference The results show that the design scheme of micro vortex generator proposed in this paper for SCCH landing configuration is validated by CFD and wind tunnel test. The maximum increase and the increase of drag are 10% 14%, which is in accordance with the design requirements of the lifting device when landing flight status. The design scheme proposed by CFD method is the best and has the uniqueness. At the same time, it also shows that the design principle, design method and technology of the micro vortex generator Route can be used for model development.