Usatrecom Technical Report 65-16 the Marvel Report Part E a Unique Solution to the Problem of Obtaining Two-dimensional Boundary Layer Data on the Variable-camber High-lift Wings of the Marvelette Aircraft

This paper reports on the design, construction, Instrumentation and preliminary testing performed on the high-lift 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.