TY - GEN
T1 - Prediction of a Laminar Separation Bubble on low-Reynolds Airfoils using Variational Multiscale Method
AU - Brunelli, Carlo
AU - Avirović, Matija
AU - Janssens, Bart
AU - Marinus, Benoît G.
AU - May, Georg
AU - Runacres, Mark
N1 - Publisher Copyright:
© 2024, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2024
Y1 - 2024
N2 - The paper presents the application of a finite element numerical approach for predicting the development and locating the Laminar Separation Bubble (LSB) on low Reynolds airfoils. The method is a linearized and segregated variation of the Variational Multi-Scale method (LS-VMS). The aim is to demonstrate the validity of this new method, overcoming the need for calibration based on experiments and/or custom-fitting transition functions. It has been tested on the SD7003 airfoil at Re = 60 000, obtaining results aligned with previously published experimental and numerical results. Furthermore, it has been tested for the DU89-134 profile, a high lift-to-drag ratio airfoil used for high-altitude pseudo-satellite applications. For this geometry, various configurations (AoA = 5◦, Re = 250 000, 500 000) compatible with low stratospheric flight have been examined and compared with RANS simulations using the γ - Reθ transitional model showing close agreement.
AB - The paper presents the application of a finite element numerical approach for predicting the development and locating the Laminar Separation Bubble (LSB) on low Reynolds airfoils. The method is a linearized and segregated variation of the Variational Multi-Scale method (LS-VMS). The aim is to demonstrate the validity of this new method, overcoming the need for calibration based on experiments and/or custom-fitting transition functions. It has been tested on the SD7003 airfoil at Re = 60 000, obtaining results aligned with previously published experimental and numerical results. Furthermore, it has been tested for the DU89-134 profile, a high lift-to-drag ratio airfoil used for high-altitude pseudo-satellite applications. For this geometry, various configurations (AoA = 5◦, Re = 250 000, 500 000) compatible with low stratospheric flight have been examined and compared with RANS simulations using the γ - Reθ transitional model showing close agreement.
UR - http://www.scopus.com/inward/record.url?scp=85203606992&partnerID=8YFLogxK
U2 - 10.2514/6.2024-4261
DO - 10.2514/6.2024-4261
M3 - Conference contribution
AN - SCOPUS:85203606992
SN - 9781624107160
T3 - AIAA Aviation Forum and ASCEND, 2024
BT - AIAA Aviation Forum and ASCEND, 2024
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Aviation Forum and ASCEND, 2024
Y2 - 29 July 2024 through 2 August 2024
ER -