Oil flow on the surface and pitot pressure measurements in the wake of a 0.762 m chord airfoil in a 8 ft x 6 ft tunnel indicate that there is no significant spanwise convergence or divergence of the flow within the boundary layer and wake of the model. The measurements were made at subsonic conditions where no regions of separated flow existed on the model, but where significant subsonic drag creep had previously been measured.
A Brief Investigation of the Two-Dimensionality of the Flow over an Airfoil in the 8 Foot by 6 Foot Transonic Wind Tunnel
1979
20 pages
Report
No indication
English
Aerodynamics , Test Facilities & Equipment , Flow visualization , Subsonic flow , Transonic wind tunnels , Two dimensional flow , Wind tunnel tests , Wing profiles , Aircraft wakes , Airfoils , Boundary layer separation , Convergence , Divergence , Pitot tubes , Pressure measurements , Foreign technology