The Study Of Aerodynamic Characteristics Of Afterbody And Effect Of Cable-Mounting
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摘要: 以民用机后体为对象，对四线、六线和八线3种张线布局对后体分离流型、旋涡结构及气动特性的影响进行了研究，实验是在北航D-1风洞中进行的，实验ReD= 2.148×105. 实验研究表明：随迎角从- 10°增加到20°，收缩上翘民用机后体的绕流涡系由下涡系转变为上涡系，直到多涡系结构，相应的分离流态由上分离流型转变为下分离流型；张线对机身后体绕流流场的影响一方面通过对绕流旋涡的干扰起作用，张线尾迹区的低能流会降低绕流旋涡对机身表面的诱导作用，采用1mm张线，对于四线、六线和八线3种支撑型式，机身后体分离流型及旋涡结构未发生明显改变.
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关键词:
- 张线支撑,气动特性,流型,分离
Abstract: The purpose of this paper is to study the effect ofcable-mounting on flow over an afterbody of a aircraft. The experimentalresults show that: (1) the flow patterns over afterbody can be divided intoupper-separated, non-separated and under-separated type; (2) thecable influences the aerodynamic characteristics of the model by affectingthe vortex structure over it; (3) the basic flow patterns overafterbody have not been changed evidently by any of these three types ofcable-mounting configuration. -
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