Transonic flow field around a fighter wing/pylon configuration was simulated by using an implicit upwinding Navier-Stokes flow solver (F3D) and overset grid technology (Chimera). Flow separation and local shocks near the wing/pylon junction were observed in flight and predicted by numerical calculations. A new pylon/fairing shape was proposed to improve the flow quality. Based on numerical results, the size of separation area is significantly reduced and the onset of separation is delayed farther downstream. A smoother pressure gradient is also obtained near the junction area. This paper demonstrates that computational fluid dynamics (CFD) methodology can be used as a practical tool for aircraft design.
Juncture flow improvement for wing/pylon configurations by using CFD methodology
AIAA, Aerospace Sciences Meeting and Exhibit ; 1993 ; Reno, NV, United States
1993-01-01
Conference paper
No indication
English
Transonic Aerodynamics of a Wing/Pylon/Strut Juncture
AIAA | 2003
|AIAA-2003-4062 Transonic Aerodynamics of a Wing/Pylon/Strut Juncture
British Library Conference Proceedings | 2003
|3D Boundary Layer Computations on Wing-Pylon-Nacelle Configurations
British Library Conference Proceedings | 1996
|