A model based on numerical solution of Navier-Stokes equations was established for hypersonic flight vehicle nozzle afterbody optimization design.The internal portion and the upper wall of nozzle were designed
and the optimized configuration was obtained.The result was compared to the norm configuration that Edwards claimed.The results show that the performance of nozzle afterbody was improved.
Building and analysis of ontology based knowledge organizationmodel for aircraft engine design
Simulation and Experiment Validation of a Two Dimensional Asymmetric Ramp Nozzle
Computation of effect of different nozzle parameters on internal performance of convergent-divergent axisymmetric nozzle
Combined heating method of low speed and high/middle temperature gas flow for thermal test of tip wedge structure
Computation and analysis of aeroheating of scramjet inlet cowl lip
Related Author
JIA Di
FAN Xiao-qiang
FENG Ding-hua
LI Hua
LI Nian
ZHANG Kun-yuan
XU Jing-lei
SHAO Wan-ren
Related Institution
College of Aerospace and Material Engineering, National University of Defense Technology
College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics
School of Jet Propulsion, Beijing University of Aeronautics and Astronautics
Shenyang Aeroengine Research Institute, Aviation Industry Corporation of China
Fundamental Science on Ergonomics and Environment Control Laboratory, School of Aeronautics Science and Engineering, Beijing University of Aeronautics and Astronautics