微修形异型转圆内转式进气道的设计与试验研究

推进技术 ›› 2017, Vol. 38 ›› Issue (6): 1218-1225.

微修形异型转圆内转式进气道的设计与试验研究

卫锋,贺旭照,陈军,吴颖川,乐嘉陵

中国空气动力研究与发展中心超高速空气动力学研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000,中国空气动力研究与发展中心超高速空气动力学研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000,中国空气动力研究与发展中心超高速空气动力学研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000,中国空气动力研究与发展中心超高速空气动力学研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000,中国空气动力研究与发展中心超高速空气动力学研究所高超声速冲压发动机技术重点实验室，四川绵阳 621000

发布日期:2021-08-15
作者简介:卫锋，男，硕士，研究领域为高超声速飞行器设计。
基金资助:
国家自然科学基金(51376192；91216303)；高超声速冲压发动机技术国防科技重点实验室绵阳分部资助项目。

Design and Experimental Study of Minimized Shape Transformation Inward Turning Inlet with Abnormity Entrance to Circle Exit

Science and Technology on Scramjet Laboratory，Hypervelocity Aerodynamics Institute CARDC，Mianyang 621000，China,Science and Technology on Scramjet Laboratory，Hypervelocity Aerodynamics Institute CARDC，Mianyang 621000，China,Science and Technology on Scramjet Laboratory，Hypervelocity Aerodynamics Institute CARDC，Mianyang 621000，China,Science and Technology on Scramjet Laboratory，Hypervelocity Aerodynamics Institute CARDC，Mianyang 621000，China and Science and Technology on Scramjet Laboratory，Hypervelocity Aerodynamics Institute CARDC，Mianyang 621000，China

Published:2021-08-15

摘要/Abstract

摘要： 利用流线追踪及微修型技术，设计了一种类水滴转圆形内转式进气道，针对该进气道开展了初步的数值与试验研究。研究结果表明:该进气道保持了流线追踪进气道前缘激波结构，微型面融合方法最大限度减少了对进气道流场的影响；Ma=6.0 /AOA=2°时，试验测得的机体/唇口侧压力分布与CFD吻合较好，隔离段出口截面皮托压分布规律基本一致，但在值域上存在一定偏差；随着攻角由-2°增至6°，唇口反射激波在机体侧的交汇点前移约55mm；堵塞度在70%～75%时，进气道最大反压约0.41MPa；进气道启动状态下，未受反压扰动点压力脉动小，波动不明显；进气道启动但受反压扰动点压力脉动增加，波动范围增大；进气道不启动状态下受扰点压力脉动大，随时间变化的周期性表现明显，低频振动明显。

关键词: 微修型；内转式进气道；设计分析；试验研究

Abstract: The Minimized Shape Transformation Inward Turning(MSTIT) inlet with water-drop like entrance to circle exit was designed by streamline-tracing and minimized shape transformation method. The preliminary aerodynamic performances of this inlet were conducted by CFD and experimental test. The results indicate that，the MSTIT inlet shock front agreed well with streamline-traced inlet，the Minimal Shape Transformation procedure minimized the shape morphing influence on the MSTIT inlet flow field. At Ma=6.0，AOA=2°，the pressure distribution derived from experiment and CFD simulation on body and cowl wall center-line fitted with each other approximately. The Pitot pressure distribution trend at the exit plane of isolate was the same with each other in spite of the difference of their absolute value. As attack angle arises from -2° to 6°，the intersection point of reflected cowl shock on body-side moves forward approximately 55mm. When the throttling area ratio varied from 70%～75%，the inlet maximum back pressure resistance ability is about 0.41MPa. When the inlet is started，the pressure fluctuation of undisturbed measuring points is small and their low frequency magnitude is not obvious. The pressure fluctuation of disturbed measuring points became bigger and low frequency vibration was appeared. When the inlet is un-started，the pressure fluctuation was much bigger，the pressure periodical fluctuation and low frequency vibration become obvious.

Key words: Minimized shape transformation；Inward turning inlet；Design method；Experimental study

卫锋,贺旭照,陈军,吴颖川,乐嘉陵. 微修形异型转圆内转式进气道的设计与试验研究[J]. 推进技术, 2017, 38(6): 1218-1225.

WEI Feng,HE Xu-zhao,CHEN Jun,WU Ying-chuan,LE Jia-ling. Design and Experimental Study of Minimized Shape Transformation Inward Turning Inlet with Abnormity Entrance to Circle Exit[J]. Journal of Propulsion Technology, 2017, 38(6): 1218-1225.

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