Proceedings of NASA Conference on Supersonic-Transport Feasibility Studies and Supporting Research, September 17-19, 1963, Langley Research Center, Langley Station, Hampton, Va: Technical Memorandum X-905 |
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aircraft Airplane Configuration altitude aluminum angle of attack aspect ratio augmentation basic boom canard climb concepts cruise curve damping deflection dihedral directional stability drag coefficient Dutch roll effects engine factors feasibility studies flap flight flow flutter fuselage handling qualities improved increase indicated inlet Langley Research Center leading edge lift coefficient lift-drag ratio load longitudinal low-speed lower Mach number maximum mission NACA nacelles NASA Langley Research NASA TM nozzle operating optimum panel parameter payload percent performance pilot pitch-up planform plug nozzle pounds presented pressure problems propulsion range reduced Reynolds number SCAT 16 SCAT configurations SCAT's shown in figure sonic sonic-boom overpressure static margin structural weight subsonic supersonic speeds supersonic transport supersonic-transport surface sweep angle take-off gross weight temperature tests thermal stress thrust tion titanium transonic Transonic Speeds trim turbofan turbojet Variable-Sweep variation warp wave drag wind-tunnel wing area
Popular passages
Page 347 - Raring, Richard H. ; Freeman, JW; Schultz, JW ; and Voorhees, HR : Progress Report of the NASA Special Committee on Materials Research for Supersonic Transports.
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Page 337 - Author N64-31220* National Aeronautics and Space Administration. Langley Research Center. Langley Station. Va. NASA RESEARCH ON MATERIALS APPLICABLE TO SUPERSONIC TRANSPORTS Herbert F Hardrath and George J. Heimeral Washington. NASA. Oct. 1964 14 p refs (NASA-TM-X-1013) OTS: $0.50 On the basis of studies on fatigue behavior, rate of fatigue crack propagation, residual static strength, and resistance to deterioration of properties due to prolonged exposure to temperature, no serious materials problems...
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Page 150 - Whitcomb, Richard T.: A Study of the Zero-Lift Drag-Rise Characteristics of Wing-Body Combinations Near the Speed of Sound.
Page i - American industry. Accordingly, last February the NASA enlisted the aid of industry for the application of its engineering know-how to study, evaluate, and compare promising conceptual designs in all the areas of concern to a practical design.
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Page 303 - It is the purpose of this paper to point out some of the elements in this reconstruction — if I am still permitted to use this word.
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