A large chord swept supercritical laminar-flow control (LFC) airfoil was designed, constructed, and tested in the Langley 8-foot Transonic Pressure Tunnel (TPT). The LFC airfoil experiment was established to provide basic information concerning the design and compatibility of high performance supercritical airfoils with suction boundary-layer control achieved through fine slots or porous surface concepts. Shockless pressure distribution was achieved. Full chord laminar flow was achieved on upper and lower surfaces. Full chord laminar flow was maintained at subcritical speeds and over large supercritical zones. Feasibility of combined suction laminarization and supercritical airfoil technology was demonstrated.
Results of LFC (Laminar Flow Control) Experiment on Slotted Swept Supercritical Airfoil in Langley's 8-Foot Transonic Pressure Tunnel
1987
17 pages
Report
Keine Angabe
Englisch
Aerodynamics , Test Facilities & Equipment , Aircraft , Fluid Mechanics , Boundary layer stability , Laminar boundary layer , Laminar flow airfoils , Porous boundary layer control , Supercritical wings , Wind tunnel tests , Boundary layer transition , Goertler instability , Mach number , Pressure distribution , Reynolds number , Suction , Transonic wind tunnels