TY - JOUR
T1 - Improved Amplification Factor Transport Transition Model for Transonic Boundary Layers
AU - Wang, Yuxuan
AU - Xu, Jiakuan
AU - Qiao, Lei
AU - Zhang, Yang
AU - Bai, Junqiang
N1 - Publisher Copyright:
© 2023, AIAA International. All rights reserved.
PY - 2023/9
Y1 - 2023/9
N2 - Linear-stability-theory-based eN method plays an important role in boundary-layer transition prediction of aeronautical flows. Based on the simplification of linear stability theory (Drela and Giles, AIAA J, 1987), the amplification factor transport (AFT) equation for Tollmien-Schlichting waves using local variables was first proposed in 2013 (Coder and Maughmer, AIAA J, 2014). However, in transonic high-Reynolds-number flows, the AFT model seriously overestimates the value of NTS. To fix this problem, we have conducted many linear stability analyses to rebuild the formulations of AFT model. Compressibility effect, which has a significant impact on the prediction of NTS value, has been considered in the improved version. Coupled with the NCF model for crossflow instabilities (Xu et al., CJA, 2020), the improved AFT model is established for transonic boundary layers. Several classic test cases are successfully employed to validate present AFT model, including a flat plate, an airfoil, an infinite swept wing, a sickled-shape wing, a 6:1 inclined prolate spheroid, the NASA Common Research Model, and ARA Transonic Swept Wing. Our prediction results show that both Tollmien-Schlichting instabilities and stationary crossflow instabilities can be captured and predicted well by the improved NTS - NCF model in subsonic and transonic boundary layers.
AB - Linear-stability-theory-based eN method plays an important role in boundary-layer transition prediction of aeronautical flows. Based on the simplification of linear stability theory (Drela and Giles, AIAA J, 1987), the amplification factor transport (AFT) equation for Tollmien-Schlichting waves using local variables was first proposed in 2013 (Coder and Maughmer, AIAA J, 2014). However, in transonic high-Reynolds-number flows, the AFT model seriously overestimates the value of NTS. To fix this problem, we have conducted many linear stability analyses to rebuild the formulations of AFT model. Compressibility effect, which has a significant impact on the prediction of NTS value, has been considered in the improved version. Coupled with the NCF model for crossflow instabilities (Xu et al., CJA, 2020), the improved AFT model is established for transonic boundary layers. Several classic test cases are successfully employed to validate present AFT model, including a flat plate, an airfoil, an infinite swept wing, a sickled-shape wing, a 6:1 inclined prolate spheroid, the NASA Common Research Model, and ARA Transonic Swept Wing. Our prediction results show that both Tollmien-Schlichting instabilities and stationary crossflow instabilities can be captured and predicted well by the improved NTS - NCF model in subsonic and transonic boundary layers.
UR - http://www.scopus.com/inward/record.url?scp=85170846868&partnerID=8YFLogxK
U2 - 10.2514/1.J062341
DO - 10.2514/1.J062341
M3 - 文章
AN - SCOPUS:85170846868
SN - 0001-1452
VL - 61
SP - 3866
EP - 3882
JO - AIAA Journal
JF - AIAA Journal
IS - 9
ER -