TY - JOUR
T1 - Improved local amplification factor transport equation for stationary crossflow instability in subsonic and transonic flows
AU - XU, Jiakuan
AU - QIAO, Lei
AU - BAI, Junqiang
N1 - Publisher Copyright:
© 2020 Chinese Society of Aeronautics and Astronautics
PY - 2020/12
Y1 - 2020/12
N2 - Transition prediction is a hot research topic of fluid mechanics. For subsonic and transonic aerodynamic flows, eN method based on Linear Stability Theory (LST) is usually adopted reliably to predict transition. In 2013, Coder and Maughmer established a transport equation for Tollmien-Schlichting (T-S) instability so that the eN method can be applied to general Reynolds-Average-Navier-Stokes (RANS) solvers conveniently. However, this equation focuses on T-S instability, and is invalid for crossflow instability induced transition which plays a crucial role in flow instability of three-dimensional boundary layers. Subsequently, a transport equation for crossflow instability was developed in 2016, which is restricted to wing-like geometries. Then, in 2019, this model was extended to arbitrarily shaped geometries based on local variables. However, there are too many tedious functions and parameters in this version, and it can only be used for incompressible flows. Hence, in this paper, after a large amount of LST analyses and parameter optimization, an improved version for subsonic and transonic boundary layers is built. The present improved model is more robust and more concise, and it can be applied widely in aeronautical flows, which has great engineering application value and significance. An extensive validation study for this improved transition model will be performed.
AB - Transition prediction is a hot research topic of fluid mechanics. For subsonic and transonic aerodynamic flows, eN method based on Linear Stability Theory (LST) is usually adopted reliably to predict transition. In 2013, Coder and Maughmer established a transport equation for Tollmien-Schlichting (T-S) instability so that the eN method can be applied to general Reynolds-Average-Navier-Stokes (RANS) solvers conveniently. However, this equation focuses on T-S instability, and is invalid for crossflow instability induced transition which plays a crucial role in flow instability of three-dimensional boundary layers. Subsequently, a transport equation for crossflow instability was developed in 2016, which is restricted to wing-like geometries. Then, in 2019, this model was extended to arbitrarily shaped geometries based on local variables. However, there are too many tedious functions and parameters in this version, and it can only be used for incompressible flows. Hence, in this paper, after a large amount of LST analyses and parameter optimization, an improved version for subsonic and transonic boundary layers is built. The present improved model is more robust and more concise, and it can be applied widely in aeronautical flows, which has great engineering application value and significance. An extensive validation study for this improved transition model will be performed.
KW - Boundary layer transition
KW - Crossflow instability
KW - Linear stability theory
KW - Transition Model
KW - Transonic flows
UR - http://www.scopus.com/inward/record.url?scp=85092035013&partnerID=8YFLogxK
U2 - 10.1016/j.cja.2020.05.012
DO - 10.1016/j.cja.2020.05.012
M3 - 文章
AN - SCOPUS:85092035013
SN - 1000-9361
VL - 33
SP - 3073
EP - 3081
JO - Chinese Journal of Aeronautics
JF - Chinese Journal of Aeronautics
IS - 12
ER -