一种腹下S弯进气道低速大攻角下气动特性实验
Investigation of pneumatic characteristics for a ventral S-shaped inlet at high incidence and low speed
-
摘要: 对一种腹下S弯进气道进行了实验研究,得到了低速大攻角下的气动特性,结果表明:随出口马赫数的增加,腹下S弯进气道出口截面的总压恢复系数不断下降,稳态周向畸变指数、紊流度和综合畸变指数均上升;出口马赫数为0.45时,进气道出口总压信号的功率谱在220Hz处存在峰值,内通道发生了局部流动分离;与地面抽吸状态相比,该进气道在低速大攻角状态下具有较高的总压恢复系数,虽综合畸变指数也偏大,但能够满足发动机正常工作的要求.Abstract: The pneumatic characteristics of a ventral S-shaped inlet at high incidence and low speed were investigated experimentally.The results show that when the Mach number Mae of the flow at the exit increases,the total pressure recovery decreases,and the circular steady total pressure distortion,turbulence intensity and synthesis distortion increase.When Mae is at 0.45,the total pressure recovery coefficient,circular steady total pressure distortion coefficient,turbulence intensity and synthesis distortion coefficient are 0.881,1.292%,1.513% and 2.805% respectively.At the same time,the power spectrum magnitude of the dynamic total pressure signals has a peak value at 220 Hz,which confirms that a flow separation occurs somewhere in the duct.As compared with the experimental result under ground running,the results at high incidence and low speed have a higher total pressure recovery and although the synthesis distortion is also higher,the inlet is fit enough to the engine at high incidence and low speed.
-
[1] Antonatos P P,Surber L E,Stava D J.Inlet/airframe interference and integration[R].AGARD-LS-53,Airframe/Engine Integration,1972. [2] Hawkins J E.YF-16 inlet design and performance[R].AIAA 74-1062. [3] Hunter L G Jr,Hawkins J E.F-16 variable-geometry inlet design and performance[R].AIAA 81-1394. [4] Walsh K R,Yuhas A J,Williams J G,et al.Steen,inlet distortion for an F/A-18A aircraft during steady aerodynamic conditions up to 60 angle of attack[R].NASA TM104329,1997. [5] 林麒,郭荣伟.大攻角下S弯进气道内气流的动特性[J].南京航空学院学报,1992,24(1):36-45.LIN Qi,GUO Rongwei.The unsteady flow characteristics of an S-shaped inlet at high incidence[J].Journal of Nanjing University of Aeronautics & Astronautics,1992,24(1):36-45.(in Chinese) [6] 林麒,郭荣伟.大攻角下矩形变圆形截面的S形进气道的内流特性[J].空气动力学学报,1989,7(2)220-226.LIN Qi,GUO Rongwei.Flow characteristicsin in an S-shaped reetangula-round diffuser at high incidence[J].Acta Aerodynamic Snica,1989,7(2) ;220-226.(in Chinese) [7] 林麒,郭荣伟.S弯进气道内漩流的有源涡控研究[J].航空学报,1989,10(1):A35-40.LIN Qi,GUO Rongwei.Vortex control investigation of swirl in S-shaped diffuser[J].Acta Aeronautics et Astronautics Sinica,1989,10(1):A35-40.(in Chinese) [8] 王琴芳.航空燃气涡轮发动机原理[M].南京:南京航空航天大学出版社,2002. [9] Amin N F,Hollweger D J.F/A-18A inlet/engine compatibility flight test results[R].AIAA-91-1393. -
点击查看大图
计量
- 文章访问数: 1704
- HTML浏览量: 194
- PDF量: 480
- 被引次数: 0
下载: