The paper reports on the design, construction, instrumentation and preliminary testing performed on the highlift wing of the MARVELETTE aircraft in a two-dimensional wind tunnel. The wind tunnel, 12 feet high and 2 feet 9 inches wide was fitted over a section of the aircraft wing to the shrouded propeller at the rear of the vehicle. When operating with this arrangement, wind tunnel velocities up to 60 miles per hour were obtainable in the test section. The tunnel provided more data in a few weeks of operation than would have been obtained in a number of months using a flight program with a considerable number of flights close to minimum flight speeds. (Author)
The Marvel Project. Part E. A Unique Solution to the Problem of Obtaining Twodimensional Boundary Layer Data on the Variable-Camber High-Lift Wings of the Marvelette Aircraft
1965
2 pages
Report
Keine Angabe
Englisch
Wings , Research planes , Aerodynamic configurations , Test facilities , Wind tunnels , Lift , Design , Construction , Instrumentation , Tests , Turbulent boundary layer , Camber , Shrouded propellers , Thrust , Effectiveness , Costs , Two-dimensional flow , Flight , Simulation , Marvel project , Marvelette aircraft
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