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An Investigation of the Trailing Vorticity Behind a STOL Aircraft.
Final rept., Sep 71-Aug 73,
MISSISSIPPI STATE UNIV STATE COLLEGE DEPT OF AEROPHYSICS AND AEROSPACE ENGINEERING
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The report presents the results of a test program to measure the near-field wake behind the wing of a test aircraft, out of the ground effect, and to obtain vortex trajectory data on trailing vortices generated within the ground effect. The test aircraft was a high-lift L-19 aircraft incorporating a distributed-suction boundary layer control system. The wake measurement probe was supported from the fuselage of the test aircraft and was mounted on a trolley which moved along a boom structure. The velocity measurements were made with a six-element hot-film anemometer. The near field wake data were obtained in two measurement planes located 0.64 and 5.10 feet behind the wing. Data were obtained at zero and fullflap deflection and true speeds of 46, 66, and 85 mph. The data are presented as contours of constant normalized vorticity, nondimensional vertical velocity, and non-dimensional longitudinal velocity increment within the measurement planes. Modified author abstract
APPROVED FOR PUBLIC RELEASE