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作 者:姚皆可 陈斌 尚银辉 郭强 YAO Jie-ke;CHEN Bin;SHANG Yin-hui;GUO Qiang(Technology Center,Chengdu Aircraft Industrial(group)CO.LTD.,Chengdu 910092,China)
机构地区:[1]成都飞机工业(集团)有限责任公司技术中心,成都610092
出 处:《航空发动机》2022年第6期18-27,共10页Aeroengine
基 金:中国航空工业集团基金资助。
摘 要:为了获得采用复杂进气道飞机全机溢流阻力产生的原因及影响溢流阻力的因素,以采用基于S形进气道的无人机为研究对象,对全机所受的气动阻力进行了分析,并给出数值计算方法;建立了带S形进气道模型的全机阻力求解方案,包括计算网格及计算设置等;选取无人机某架次空中停车状态为研究对象,对进气道出口的总压恢复系数分布及溢流阻力进行计算,并与缩比模型测压风洞试验结果及飞参辨识所获得的溢流阻力进行对比,验证了数值方法的可行性;针对流量系数、马赫数、迎角及侧滑角对溢流阻力的影响进行分析,结果表明:当流量系数减小时,进气道内外的压力差及S形内管道的弯曲引起的逆压梯度变大,使得捕获流管变细,从而导致附加阻力和溢流阻力均增大;当飞行马赫数增大时,发动机需求的流量增加,从进气道溢出的气流减少,导致溢流阻力减小。从而确定对溢流阻力影响较大的2个主要因素为流量系数和马赫数。To obtain the causes and influencing factors of the spillage drag of an aircraft equipped with complex intake,aerodynamic drags of a UAV with s-shaped intake were analyzed,and numerical calculation methods were given. The model of aircraft with of S-shaped intake for drag accounting was established,including computational grid,simulation settings,etc. Numerical calculations of total pressure recovery coefficient and spillage drag were conducted for an in-flight shutdown state of the UAV,calculation results were compared with the results of wind tunnel scale model test and flight test parameter identification,and the feasibility of the numerical method was verified by the comparison. Influencing factors of spillage drag such as mass flow ratio,Mach numbers,angle of attack and sideslip angle were investigated. The results show that as the mass flow ratio decreases,the pressure difference inside and outside the intake and the higher adverse pressure gradient caused by the bending of the S-shaped duct lead to the reduction of the capture stream tube,and the increase of the additive drag and spillage drag. As the flight Mach number increases,the flow required by the engine increases,and the airflow spilled from the intake is reduced,thus leading to the reduction of the spillage drag. Therefore,it is determined that the mass flow ratio and Mach number are the two main factors that have a greater impact on the spillage drag.
关 键 词:S形进气道 溢流阻力 附加阻力 流量系数 数值仿真 飞/发匹配
分 类 号:V211.3[航空宇航科学与技术—航空宇航推进理论与工程]
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