Calculations have been made of the three-dimensional, compressible, turbulent boundary layer on the finite supercritical wing of the NASA modified F-8 transonic research airplane. The calculations were based on the wing pressure distribution measured in flight at M = 0.90, instead of on wind tunnel data at M = 0.50 and 0.99. Data on the boundary-layer thickness, displacement thickness, skin-friction components, and integrated streamwise skin friction are presented for points along the streamwise stations at which pressure measurements were made.
Additional three-dimensional boundary-layer computations for a finite swept wing
1972-01-01
Report
No indication
English
Three-Dimensional Boundary-Layer Transition on a Swept Wing at Mach 3.5
Online Contents | 1995
|Computations of Swept Wing Icing Aerodynamics
AIAA | 2019
|BOUNDARY-LAYER RECEPTIVITY OF THREE-DIMENSIONAL ROUGHNESS ARRAYS ON A SWEPT-WING
British Library Conference Proceedings | 2011
|