发动机短舱安装位置对民机气动性能参数影响
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摘要
为研究不同发动机短舱位置对民用飞机的气动性能影响,定义短舱位于机翼前方、正下方、后方分别为A、B、C,机身尾部为D,基于RANS方程,采用Fluent数值分析了A、B、C、D的流场。结果表明,位置A和D对压力云图的影响较小,B和C会产生高压区而增加阻力;位置A和D具有较优的气动性能,阻力系数较小,4°迎角时,位置A相对C的阻力系数降低了12.5%,同时在典型状态上也具有较高的气动性能。研究结果可为民用飞机的短舱位置选择提供技术参考。
In order to study the influence of different engine nacelle positions on aerodynamic performance of civil aircraft,the nacelle position which is located respectively in front of,directly below,and behind the wing were defined as A,B,C,and nacelle position which is located in the tail of fuselage is defined as D.The flow fields of A,B,C,and D were analyzed by Fluent according to RANS equations.The results show that there exists less influence on the pressure contour in position A and D,and the high pressure zone is appeared in B and C to increase drag.Position A and D possess better aerodynamic performance with smaller drag coefficient.Compared with C,the drag coefficient of A is reduced 12.5% with angle of attack is 4°,and it also has a better aerodynamic performance in other typical states.The results of the study can be provided as technical reference for the nacelle position for civil aircraft.
In order to study the influence of different engine nacelle positions on aerodynamic performance of civil aircraft,the nacelle position which is located respectively in front of,directly below,and behind the wing were defined as A,B,C,and nacelle position which is located in the tail of fuselage is defined as D.The flow fields of A,B,C,and D were analyzed by Fluent according to RANS equations.The results show that there exists less influence on the pressure contour in position A and D,and the high pressure zone is appeared in B and C to increase drag.Position A and D possess better aerodynamic performance with smaller drag coefficient.Compared with C,the drag coefficient of A is reduced 12.5% with angle of attack is 4°,and it also has a better aerodynamic performance in other typical states.The results of the study can be provided as technical reference for the nacelle position for civil aircraft.
引文
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[9]张宏,颜洪.DLR-F6复杂组合体跨声速阻力计算研究[J].哈尔滨工程大学学报,2013,34(3):325-331.
[10]Panagiotou P,Kaparos P,Salpingidou C.Aerodynamic design of a MALE UAV[J].Aerospace Science and Technology,2016,50(1):127-128.
[2]张帅,夏明,钟伯文.民用飞机气动布局发展演变及其技术影响因素[J].航空学报,2016,37(1):30-44.
[3]党亚斌,刘凯礼,谭兆光,等.民用飞机尾吊发动机安装效应对推力影响研究[J].推进技术,2018,39(8):1712-1719.
[4]Zhou Zeyang,Huang Jun,Yi Mingxu.Comprehensive optimization of aerodynamic noise and radar stealth for helicopter rotor based on Pareto solution[J].Aerospace Science and Technology,2018,83(5):607-619.
[5]Ishide T,Itazawa M.Aerodynamic improvement of a delta wing in combination with leading edge flaps[J].Theoretical&Applied Mechanics Letters,2017,30(7):357-361.
[6]邱亚松,白俊强,黄琳,等.翼吊发动机短舱对三维增升装置的影响及改善措施研究[J].空气动力学学报,2012,30(1):7-13.
[7]Zhao Kun,Alimohammadi S,Patrick N,et al.Aerodynamic noise reduction using dual-jet planar air curtains[J].Journal of Sound and Vibration,2018,423(2):192-212.
[8]闫文辉,薛然然.NACA4412翼型低速绕流数值计算中湍流模型对比[J].航空学报,2017,38(S1):33-40.
[9]张宏,颜洪.DLR-F6复杂组合体跨声速阻力计算研究[J].哈尔滨工程大学学报,2013,34(3):325-331.
[10]Panagiotou P,Kaparos P,Salpingidou C.Aerodynamic design of a MALE UAV[J].Aerospace Science and Technology,2016,50(1):127-128.