TY - GEN
T1 - A comparison study on transition characteristics of NLF forward-swept-wing and aft-swept-wing
AU - Zhu, Zhen
AU - Song, Wen Ping
AU - Han, Zhong Hua
AU - Xu, Jian Hua
N1 - Publisher Copyright:
© 31st Congress of the International Council of the Aeronautical Sciences, ICAS 2018. All rights reserved.
PY - 2018
Y1 - 2018
N2 - The forward-swept-wing (FSW) is a favorable concept in natural laminar flow (NLF) wing design. It has smaller leading edge swept angle λ LE than that of aft-swept-wing (ASW), which may avoid leading edge transition induced by cross flow (CF) instability. However, there are still some key technological issues, such as the characteristics of boundary layer transition in transonic flow, aerodynamic performances and the differences of CF instability between FSW and ASW, are not clear. A comparison study on transition characteristics, boundary layer stability and aerodynamic performances of NLF FSW and ASW is carried out. A three-dimensional Reynolds-averaged Navier-Stokes (RANS) solver coupled with a dual e N transition prediction method based on linear stability theory (LST) is used. Fixed wave angle method and fixed wave number method are employed for Tollmien-Schlichting (TS) instability and cross-flow instability, respectively. The results show that, 1). With the same λ LE , the FSW in this paper has a smaller CF instability and larger area of laminar flow than that of ASW. 2). Compared with ASW, the FSW has larger swept angle at about 50%-60% chord where shock wave may occur, which leads to much weaker shock wave. 3). C L /C D of the FSW is 13.7% larger than that of ASW. It can be concluded that FSW has more advantages in NLF supercritical wing design.
AB - The forward-swept-wing (FSW) is a favorable concept in natural laminar flow (NLF) wing design. It has smaller leading edge swept angle λ LE than that of aft-swept-wing (ASW), which may avoid leading edge transition induced by cross flow (CF) instability. However, there are still some key technological issues, such as the characteristics of boundary layer transition in transonic flow, aerodynamic performances and the differences of CF instability between FSW and ASW, are not clear. A comparison study on transition characteristics, boundary layer stability and aerodynamic performances of NLF FSW and ASW is carried out. A three-dimensional Reynolds-averaged Navier-Stokes (RANS) solver coupled with a dual e N transition prediction method based on linear stability theory (LST) is used. Fixed wave angle method and fixed wave number method are employed for Tollmien-Schlichting (TS) instability and cross-flow instability, respectively. The results show that, 1). With the same λ LE , the FSW in this paper has a smaller CF instability and larger area of laminar flow than that of ASW. 2). Compared with ASW, the FSW has larger swept angle at about 50%-60% chord where shock wave may occur, which leads to much weaker shock wave. 3). C L /C D of the FSW is 13.7% larger than that of ASW. It can be concluded that FSW has more advantages in NLF supercritical wing design.
KW - Cross flow instability
KW - E method
KW - Forward-swept wing
KW - Natural laminar flow
KW - Transition prediction
UR - http://www.scopus.com/inward/record.url?scp=85060490895&partnerID=8YFLogxK
M3 - 会议稿件
AN - SCOPUS:85060490895
T3 - 31st Congress of the International Council of the Aeronautical Sciences, ICAS 2018
BT - 31st Congress of the International Council of the Aeronautical Sciences, ICAS 2018
PB - International Council of the Aeronautical Sciences
T2 - 31st Congress of the International Council of the Aeronautical Sciences, ICAS 2018
Y2 - 9 September 2018 through 14 September 2018
ER -