and a compared bell nozzle were designed to gain the performance characteristics of plug nozzle.The thrust performances of the nozzles were evaluated with numerical simulation method.A ground hot test was done to measure the thrust performance the clustered plug nozzle.The result shows that the numerical simulation results of the flow phenomenon and thrust performance accord with the experimental results.The thrust efficient of the plug nozzle in ground reaches 92.6% and is 9.1% higher than the bell nozzle with the same area ratio and length
reflecting the altitude compensation effects of plug nozzle.However
its thrust efficient in high attitude is 5.8% lower than the compared bell nozzle.
Progress of investigation on combustion instability of solid rocket motors
Steady numerical study of aerodynamic throat formed by round injectors
Structural analysis of aged grain of solid rocket motor with crack
Effects of loading distribution on a vaned diffuser
Influence of suction-side winglet length on tip leakage flow in compressor cascade
Related Author
WANG Ning-fei
ZHANG Qiao
LI Jun-wei
SU Wan-xing
WANG Yi-bai
ZHANG Jian-wei
ZHI Shi-jun
SUN Bing
Related Institution
School of Aerospace Engineering, Beijing Institute of Technology
National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Jet Propulsion, Beijing University of Aeronautics and Astronautics
School of Energy Science and Engineering, Harbin Institute of Technology
Marine Engineering College, Dalian Maritime University
Graduate University of Chinese Academy of Sciences