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Transonic Aerodynamics Characteristics of a Supersonic Cruise Aircraft Research Model with the Engines Suspended Above the Wing

出版	National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1979
URL	http://books.google.com.hk/books?id=ryoCAAAAIAAJ&hl=&source=gbs_api

註釋An investigation was conducted in the Langley ]6-foot transonic tunnel to determine the influence of upper-surface nacelle exhaust flow on the aerodynamic characteristics of a supersonic cruise aircraft research configuration over a range of Mach numbers from 0.60 to 1.20. The arrow-wing transport configuration with engines suspended over the wing was tested at angles of attack from -4 ° to 6° and jet total-pressure ratios from ] to approximately 13. Wing-tip leading edge flap deflections of -10 ° to ]0 ° were tested with the wing-body configuration. Various nacelle locations (chordwise, spanwise, and vertical) were tested over the ranges of Mach numbers, angles of attack, and jet total-pressure ratios.