The Online Books Page

Online Books by

Odell A. Morris

Books from the extended shelves:

• Morris, Odell A.: Aerodynamic characteristics in pitch at a Mach number of 1.97 of two variable-wing- sweep V/STOL configurations with outboard wing panels swept back 75 degree (National Aeronautics and Space Administration, 1960), also by Gerald V. Foster, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Morris, Odell A.: Aerodynamic characteristics in pitch of several ring-wing-body configurations at a mach number of 2.2. Odell Morris. (National Aeronautics and Space Administration :, 1962), also by United States National Aeronautics and Space Administration (page images at HathiTrust)
• Morris, Odell A.: Aerodynamic characteristics of a fixed arrow-wing supersonic cruise aircraft at Mach numbers of 2.30, 2.70, and 2.95 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), also by Crolyn B. Watson, Dennis E. Fuller, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Morris, Odell A.: Aerodynamic characteristics of a parasol-wing--body combination utilizing favorable lift interference at Mach numbers from 3.00 to 4.63 (National Aeronautics and Space Administration ;, 1968), also by Robert J. Mack, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Morris, Odell A.: Aerodynamic characteristics of a three-engine supersonic transport model having a low-aspect-ratio variable-sweep warped wing (National Aeronautics and Space Administration, 1964), also by Dennis E. Fuller and Langley Research Center (page images at HathiTrust)
• Morris, Odell A.: Aerodynamic tests and analysis of a turbojet-boosted launch vehicleconcept (spacejet) over a Mach number range of 1.50 to 2.86 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), also by Gregory D. Riebe, William J. Small, Langley Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Morris, Odell A.: Control hinge-movement and effectiveness characteristics of several interchangeable tip controls on a 60©� delta wing at Mach numbers of 1.41, 1.62, and 1.96 (Washington, D.C. : National Advisory Committee for Aeronautics, 1953., 1953), also by Langley Aeronautical Laboratory and United States. National Advisory Committee for Aeronautics (page images at HathiTrust)
• Morris, Odell A.: Experimental effects of fuselage camber on longitudinal aerodynamic characteristics of a series of wing-fuselage configurations at a mach of 1.41 (U.S. National Aeronautics and Space Administration ;, 1976), also by Samuel M. Dollyhigh, Mary S. Adams, United States National Aeronautics and Space Administration, and Langley Research Center (page images at HathiTrust)
• Morris, Odell A.: Investigation of light source and scattering medium related to vapor-screen flow visualization in a supersonic wind tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), also by W. L. Snow and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Morris, Odell A.: NASA TN D-1823 (National Aeronautics and Space Administration, 1963), also by Langley Research Center and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• Morris, Odell A.: Sonic-boom characteristics in the extreme near field of a complex airplane model at mach numbers of 1.5, 1.8, and 2.5 (National Aeronautics and Space Administration, 1970), also by Harry W. Carlson, Milton Lamb, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Morris, Odell A.: Stability and control characteristics at a Mach number of 1.97 of an airplane configuration having two types of variable- sweep wings (National Aeronautics and Space Administration, 1960), also by Gerald V. Foster, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Morris, Odell A.: Static longitudinal and lateral aerodynamic characteristics at a Mach number of 2.20 of a V/STOL airplane configuration with a variable-sweep wing and with a skewed wing design (National Aeronautics and Space Administration, 1961), also by Gerald V. Foster and Langley Research Center (page images at HathiTrust)
• Morris, Odell A.: Static longitudinal and lateral aerodynamic characteristics at a Mach number of 2.20 of a variable-wing-sweep STOL configuration (National Aeronautics and Space Administration, 1960), also by Gerald V. Foster, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Morris, Odell A.: Subsonic and supersonic aerodynamic characteristics of a supersonic cruise fighter model with a twisted and cambered wing with 74 ̊sweep (National Aeronautics and Space Administration ;, 1977), also by United States National Aeronautics and Space Administration (page images at HathiTrust)
• Morris, Odell A.: Vapor-screen technique for flow visualization in the Langley Unitary Plan Wind Tunnel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), also by Langley Research Center (page images at HathiTrust)
• Morris, Odell A.: A wind-tunnel investigation at a Mach number of 2.01 of the sonic-boom characteristics of three wing-body combinations differing in wing longitudinal location (National Aeronautics and Space Administration :, 1962), also by United States National Aeronautics and Space Administration (page images at HathiTrust)
• Morris, Odell A.: Wind-tunnel investigation of sonic-boom characteristics of two simple wing models at Mach numbers from 2.3 to 4.63 (National Aeronautics and Space Administration, 1971), also by Davis S. Miller, Harry W. Carlson, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Morris, Odell A.: A wind-tunnel investigation of the effect of body shape on sonic-boom pressure distributions (National Aeronautics and Space Administration, 1965), also by Harry W. Carlson, Robert J. Mack, Langley Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)

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