A side-mounted subsonic inlet of unmanned aerial vehicle (UAV) was designed and the flow field was simulated.The characteristics of the inlet were obtained.The results show that
the inlet lip
the junction of the duct and the engine hub have great influence on the flow filed and characteristics of the inlet.The engine hub can improve the quality of the flow field at the exit of the inlet and reduce the distortion index.The total pressure recovery coefficient of the inlet is more than 0.97 and the distortion index is less than 0.15.The inlet meets the requirements of the engine at all states.
Experimental study of a serpentine inlet under ground running
Effects of loading distribution on a vaned diffuser
Influence of suction-side winglet length on tip leakage flow in compressor cascade
Numerical simulation and hot test investigation of plug nozzle in solid rocket motor
Analysis of characteristic and mechanism of pipe diffuser for a highly loaded centrifugal compressor
Related Author
JING Jian-peng
GUO Rong-wei
CAO Si
LIU Bao-jie
HAN Shao-bing
ZHONG Jing-jun
YAN Hong-ming
REN Jun-xue
Related Institution
College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics
Marine Engineering College, Dalian Maritime University
School of Energy Science and Engineering, Harbin Institute of Technology
School of Astronautics, Beijing University of Aeronautics and Astronautics