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  • 1
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    Study of the application of advanced technologies to long-range transport aircraft. Volume 2: Research and development requirements (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Investigations were conducted to evaluate the relative benefits attainable through the exploitation of advanced technologies and to identify future research and development efforts required to permit the application of selected technologies to transport aircraft entering commercial operation in 1985. Results show that technology advances, particularly in the areas of composite materials, supercritical aerodynamics, and active control systems, will permit the development of long-range, high-payload commercial transports operating at high-subsonic speeds with direct operating costs lower than those of current aircraft. These advanced transports also achieve lower noise levels and lower engine pollutant emissions than current transports. Research and development efforts, including analytical investigations, laboratory test programs, and flight test programs, are required in essentially all technology areas to achieve the potential technology benefits.
    Keywords: AIRCRAFT
    Type: NASA-CR-112089
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Application of active controls technology to the NASA Jet Star airplane (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The feasibility was studied of modifying a Jet Star airplane into a demonstrator of benefits to be achieved from incorporating active control concepts in the preliminary design of transport type aircraft. Substantial benefits are shown in terms of fuel economy and community noise by virtue of reduction in induced drag through use of a high aspect ratio wing which is made possible by a gust alleviation system. An intermediate configuration was defined which helps to isolate the benefits produced by active controls technology from those due to other configuration variables. Also, an alternate configuration which incorporated composite structures, but not active controls technology, was defined in order to compare the benefits of composite structures with those of active controls technology.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-2561 , H-868
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Feasibility study of the transonic biplane concept for transport aircraft application (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Investigations were conducted to evaluate the feasibility of a transonic biplane consisting of a forward-mounted swept-back lower wing, a rear-mounted swept-forward upper wing, and a vertical fin connecting the wings at their tips. This wing arrangement results in significant reductions in induced drag relative to a monoplane designed with the same span, and it allows for a constant-section fuselage shape while closely matching an ideal area distribution curve for M = 0.95 cruise. However, no significant reductions in ramp weight were achieved for the biplane relative to a monoplane with the same mission capability. Flutter analyses of the biplane revealed both symmetric and antisymmetric instabilities that occur well below the required flutter speed. Further studies will be required to determine if acceptable flutter speeds can be achieved through the elimination of the instabilities by passive means or by active controls. Configurations designed for other missions, especially those with lower Mach numbers and lower dynamic pressures, should be examined since the geometries suitable for those design constraints might avoid the weight penalties and flutter instabilities which prevent exploitation of induced drag benefits for the configuration studied.
    Keywords: AIRCRAFT
    Type: NASA-CR-132462 , LG74ER0077
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Advanced turboprop testbed systems study. Volume 1: Testbed program objectives and priorities, drive system and aircraft design studies, evaluation and recommendations and wind tunnel test plans (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The establishment of propfan technology readiness was determined and candidate drive systems for propfan application were identified. Candidate testbed aircraft were investigated for testbed aircraft suitability and four aircraft selected as possible propfan testbed vehicles. An evaluation of the four candidates was performed and the Boeing KC-135A and the Gulfstream American Gulfstream II recommended as the most suitable aircraft for test application. Conceptual designs of the two recommended aircraft were performed and cost and schedule data for the entire testbed program were generated. The program total cost was estimated and a wind tunnel program cost and schedule is generated in support of the testbed program.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-167928-VOL-1 , NAS 1.26:167928-VOL-1 , LG81ER0202-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    An Analytical Study for Subsonic Oblique Wing Transport Concept (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: For abstract, see N77-10045.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-137897 , LG76ER0156-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    An Analytical Study for Subsonic Oblique Wing Transport Concept (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The oblique wing concept has been investigated for subsonic transport application for a cruise Mach number of 0.95. Three different mission applications were considered and the concept analyzed against the selected mission requirements. Configuration studies determined the best area of applicability to be a commercial passenger transport mission. The critical parameter for the oblique wing concept was found to be aspect ratio which was limited to a value of 6.0 due to aeroelastic divergence. Comparison of the concept final configuration was made with fixed winged configurations designed to cruise at Mach 0.85 and 0.95. The crossover Mach number for the oblique wing concept was found to be Mach 0.91 for takeoff gross weight and direct operating cost. Benefits include reduced takeoff distance, installed thrust and mission block fuel and improved community noise characteristics. The variable geometry feature enables the final configuration to increase range by 10% at Mach 0.712 and to increase endurance by as much as 44%.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-137896 , LG76ER0156-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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