TY - GEN
T1 - Study on Flow Characteristics of Compressible Laminar Flow Boundary Layers
AU - Chang, Min
AU - Meng, Xiao Xuan
AU - Fu, Ziyuan
AU - Bai, Junqiang
N1 - Publisher Copyright:
© 2019, Springer Nature Singapore Pte Ltd.
PY - 2019
Y1 - 2019
N2 - The turbulence-transition model developed from the RANS methods has become the most used model in studying flow transition of hypersonic flight vehicles since it overcomes the flaw of stability analysis method that large-scale distributed parallel computing is not applicable. The current turbulence-transition model makes a numerical correction on compressibility in the prediction of transition within the hypersonic boundary layer, resulting in poor generality, so it needs to be further improved and perfected. Targeting this, the equations for the dimensionless boundary layer of compressible flow with pressure gradient are established, with the velocity profile and temperature profile similar outcome of the laminar plate obtained using the local similarity method. The influence of Mach number and pressure gradient on key parameters such as momentum loss thickness and shape factor are explored. The simulation results show that pressure gradient is the key factor for judging transition of the boundary layer. A new fitting equation for determining hypersonic transition model is established.
AB - The turbulence-transition model developed from the RANS methods has become the most used model in studying flow transition of hypersonic flight vehicles since it overcomes the flaw of stability analysis method that large-scale distributed parallel computing is not applicable. The current turbulence-transition model makes a numerical correction on compressibility in the prediction of transition within the hypersonic boundary layer, resulting in poor generality, so it needs to be further improved and perfected. Targeting this, the equations for the dimensionless boundary layer of compressible flow with pressure gradient are established, with the velocity profile and temperature profile similar outcome of the laminar plate obtained using the local similarity method. The influence of Mach number and pressure gradient on key parameters such as momentum loss thickness and shape factor are explored. The simulation results show that pressure gradient is the key factor for judging transition of the boundary layer. A new fitting equation for determining hypersonic transition model is established.
KW - Boundary layer transition
KW - Compressible boundary layer similarity transformation equations
KW - Self-similar solution
KW - Similarity temperature profile
KW - Similarity velocity profile
UR - http://www.scopus.com/inward/record.url?scp=85070774673&partnerID=8YFLogxK
U2 - 10.1007/978-981-13-3305-7_37
DO - 10.1007/978-981-13-3305-7_37
M3 - 会议稿件
AN - SCOPUS:85070774673
SN - 9789811333040
T3 - Lecture Notes in Electrical Engineering
SP - 451
EP - 463
BT - The Proceedings of the Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018
A2 - Zhang, Xinguo
PB - Springer Verlag
T2 - Asia-Pacific International Symposium on Aerospace Technology, APISAT 2018
Y2 - 16 October 2018 through 18 October 2018
ER -