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  • AIRCRAFT DESIGN, TESTING AND PERFORMANCE  (49)
  • 1975-1979  (49)
  • 1975  (49)
  • 1
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    Design definition study of a NASA/Navy lift/cruise fan technology V/STOL airplane: Risk assessment addendum to the final report (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An assessment of risk, in terms of delivery delays, cost overrun, and performance achievement, associated with the V/STOL technology airplane is presented. The risk is discussed in terms of weight, structure, aerodynamics, propulsion, mechanical drive, and flight controls. The analysis ensures that risks associated with the design and development of the airplane will be eliminated in the course of the program and a useful technology airplane that meets the predicted cost, schedule, and performance can be produced.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-137729 , D6-42611-ADD
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    High performance dash on warning air mobile, missile system (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An aircraft-missile system which performs a high acceleration takeoff followed by a supersonic dash to a 'safe' distance from the launch site is presented. Topics considered are: (1) technological feasibility to the dash on warning concept; (2) aircraft and boost trajectory requirements; and (3) partial cost estimates for a fleet of aircraft which provide 200 missiles on airborne alert. Various aircraft boost propulsion systems were studied such as an unstaged cryogenic rocket, an unstaged storable liquid, and a solid rocket staged system. Various wing planforms were also studied. Vehicle gross weights are given. The results indicate that the dash on warning concept will meet expected performance criteria, and can be implemented using existing technology, such as all-aluminum aircraft and existing high-bypass-ratio turbofan engines.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-TM-X-62479 , A-6260
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Multivariate Analysis, Retrieval, and Storage System (MARS). Volume 4: Turbojet and Turbofan Data Base (By Engine) (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A partial listing of turbojet and turbofan engine specifications data, as provided by the MARS (Multivariable Data Analysis, Retrieval, and Storage) system, was given for a number of engines.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-137674
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Update on an investigation of flight buffeting of a variable-sweep aircraft (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A detailed investigation of flight buffeting response of an F-111A aircraft was performed. AIAA Paper No. 74-358 presented results of an initial study of wing and fuselage responses measured at subsonic speeds and wing leading-edge sweep of 26 degrees. The present paper gives additional results for wing sweeps of 26, 50 and 72.5 degrees at Mach numbers up to 1.2 including horizontal tail responses. Power spectra, response time histories, variations of rms response with angle of attack, and effects of Mach number and wing sweep angle are discussed.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 75-68 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Rotary-wing aircraft systems for the short-haul market (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-08-13
    Description: This paper describes preliminary designs of tilt-rotor and tandem-rotor helicopter V/STOL aircraft for the 1958 short-haul market. These designs include a tilt-rotor aircraft designed for STOL-only operation. The baseline designs are presented with technological and cost data. The impact of noise and ride qualities on aircraft size and cost, and on passenger acceptance are discussed. The results of the study are compared against competitive alternatives in air transportation.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 75-275 , American Institute of Aeronautics and Astronautics, Annual Meeting and Technical Display; Feb 24, 1975 - Feb 26, 1975; Washington, DC
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Compatibility of take-off and landing with mission and manoeuvre performance requirements for fighter aircraft (1975)
    In:  CASI
    Details
    Publication Date: 2012-05-22
    Description: By means of an aircraft synthesis program, the effect of engine cycle, thrust to weight ratio, and wing parameter combination on field and flight performance has been investigated. For three different engine/intake configurations, thrust to weight ration and wing loading were varied. Each combination represents an aircraft designed to meet a specified mission radius. Using different lift systems and ground deceleration devices, the conditions are shown under which a matching of flight and field performance is economically feasible.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AGARD Take-off and Landing; 7 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Computer aided flexible envelope designs (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Computer aided design methods are presented for the design and construction of strong, lightweight structures which require complex and precise geometric definition. The first, flexible structures, is a unique system of modeling folded plate structures and space frames. It is possible to continuously vary the geometry of a space frame to produce large, clear spans with curvature. The second method deals with developable surfaces, where both folding and bending are explored with the observed constraint of available building materials, and what minimal distortion result in maximum design capability. Alternative inexpensive fabrication techniques are being developed to achieve computer defined enclosures which are extremely lightweight and mathematically highly precise.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: MIT Proc. of the Interagency Workshop on Lighter than Air Vehicles; p 209-215
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Propulsion airframe integration (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Wind tunnel simulation tests are reported that utilize a 20 inch powered nacelle for airframe integration studies. Considered are: effects of boattail positioning, nacelle size, aft fuselage drag, over-the-wing half span model installation, and turboprop and ducted fan configurations.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Kansas Univ. Proc. of the NASA, Ind., Univ., Gen. Aviation Drag Reduction Workshop; p 387-402
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    The Slate all metal airship (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The development of the Slate all metal airship City of Glendale built and completed in 1930 is presented. The airship facilities are discussed. Pertinent data which led to other engineering accomplishments for aviation are shown. The SMD-100 concept is presented along with a brief commentary on the costs and problems involved in such an airship design and the application of the hoisting and elevator facilities to airship development.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: MIT Proc. of the Interagency Workshop on Lighter than Air Vehicles; p 323-330
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    LTA application of a long trailing wire high speed/low weight reeling system (1975)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The successful development of a unique yet simple reeling system for handling long trailing tensile members at high speeds is described. This high speed when combined with the system simplicity, low weight and effective motive power consumption make this reeling system particularly attractive to LTA planners and designers for numerous LTA missions.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: MIT Proc. of the Interagency Workshop on Lighter than Air Vehicles; p 217-222
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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