A Ventral Diverterless High Offset S-shaped Inlet at Transonic Speeds
An investigation on the ventral diverterless high offset S-shaped inlet is carried out at Mach numbers from 0.600 to 1.534,angles of attack from -4° to 9.4°,and yaw angles from 0° to 8°.Results indicate:(1) a large region of low total pressure exists at the lower part of the inlet exit caused by the counter-rotating vortices in the S-shaped duct;(2) the performances of the inlet at Mach number 1.000roach almost the highest,so the propulsion system could work efficiently in terms of aerodynamics;(3) the total pressure recovery increases slowly at first and then remains unvaried as the Mach number rises from 0.6 to 1.0,however,it does in an opposite manner in the conventional diverter-equipped S-shaped inlet;(4) the performances of the inlet are generally insensitive to angles of attack from -4° to 9.4° and yaw angles from 0° to 8° at Mach number 0.850,and angles of attack from -2° to 6~ and yaw angles from 0° to 5° at Mach number 1.534.
作 者： Xie Wenzhong Guo Rongwei 作者单位： College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China 刊 名： 中国航空学报（英文版） ISTIC 英文刊名： CHINESE JOURNAL OF AERONAUTICS 年，卷(期)： 2008 21(3) 分类号： V2 关键词： aerospace propulsion system diverterless inlet high offset transonic inlet S-shaped inlet experimental investigation