WIND TUNNEL TEST REPORT CONVENTIONAL MODEL. VOLUME 3. HIGH SPEED (MACH = 0.4 TO 0.9)
GENERAL ELECTRIC CO CINCINNATI OH ADVANCED ENGINE AND TECHNOLOGY DEPT
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The volume presents the results of high speed wind tunnel test of a one-eighth scale model of the U.S. Army XV-5A Lift Fan Research Aircraft. The tests were conducted at the David Taylor Model Basin 7 x 10 foot Transonic Wind Tunnel Facility. Conventional model force, pressure, and hinge moment data were obtained over a Mach number range of .40 to .90 and pitch and sideslip ranges of -4 to 15 degrees and -5 to 5 degrees respectively. The complete aircraft was the primary configuration tested, with the majority of the variations being in control surface and stabilizer settings. Tests were also conducted with the vertical and horizontal tail surfaces removed, with wing fan upper and lower surface strut fairings removed, and with engine duct pressure survey rake installed.
- Research and Experimental Aircraft