An implicit algorithm for solving three-dimensional viscous compressible flow on unstructured grids was described.Newton's method and Roe approximate scheme which was used to evaluate the flux Jacobians were chosen to solve Navier-Stokes equations.Three representative flow cases including plate
transonic turbine vane Mark-Ⅱ and CW-22 were simulated.The results of numerical simulation show favorable agreement with exact solution in theory and experimental data
and the flow phenomena such as shock and secondary flow were predicted accurately.These suggest that this unstructured implicit Navier-Stokes flow solver can predict aerodynamic performance correctly.
Simulation method of short crack propagation in turbine disks based on crystal plasticity
Numerical simulation of internal flow field in gas generator of fire extinguishing bomb
Numerical simulation of light-craft effects onlaser supported donation wave with gas-liquid two phase propellant
Low-Reynolds-number wake flows of a triangular prism
Influence of combustor shape on self-ignition in solid fuel scramjet
Related Author
Ping ZHANG
Shan LU
Xin JING
Mao YANG
Zhongbing LUO
Rongxin ZHOU
Yunfeng LI
Kangqing DENG
Related Institution
School of Power and Energy,Northwestern Polytechnical University
Nondestructive Testing and Evaluation Laboratory, Dalian University of Technology
College of Civil Engineering, Hefei University of Technology
Key Laboratory of Aerospace Chemical Power Technology, Hubei Institute of Aerospace Chemical Techologh, China Aerospace Science and Technology Corporation,Xiangyang Hubei
Hubei Institute of Aerospace Chemistry Technology, China Aerospace Science and Technology Corporation,Xiangyang Hubei