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  • 1
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    Advanced structures technology applied to a supersonic cruise arrow-wing configuration (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: The application of advanced technology to a promising aerodynamic configuration was explored to investigate the improved payload range characteristics over the configuration postulated during the National SST Program. The results of an analytical study performed to determine the best structural approach for design of a Mach number 2.7 arrow-wing supersonic cruise aircraft are highlighted. The data conducted under the auspices of the Structures Directorate of the National Aeronautics and Space Administration, Langley Research Center, established firm technical bases from which further trend studies were conducted to quantitatively assess the benefits and feasibility of using advanced structures technology to arrive at a viable advanced supersonic cruise aircraft.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA. Langley Res. Center Proc. of the SCAR Conf., Pt. 2,; 34 p
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Arrow-wing supersonic cruise aircraft structural design concepts evaluation. Volume 1: Sections 1 through 6 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The structural approach best suited for the design of a Mach 2.7 arrow-wing supersonic cruise aircraft was investigated. Results, procedures, and principal justification of results are presented. Detailed substantiation data are given. In general, each major analysis is presented sequentially in separate sections to provide continuity in the flow of the design concepts analysis effort. In addition to the design concepts evaluation and the detailed engineering design analyses, supporting tasks encompassing: (1) the controls system development; (2) the propulsion-airframe integration study; and (3) the advanced technology assessment are presented.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-132575-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Arrow-wing supersonic cruise aircraft structural design concepts evaluation. Volume 3: Sections 12 through 14 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The design of an economically viable supersonic cruise aircraft requires the lowest attainable structural-mass fraction commensurate with the selected near-term structural material technology. To achieve this goal of minimum structural-mass fraction, various combinations of promising wing and fuselage primary structure were analyzed for the load-temperature environment applicable to the arrow wing configuration. This analysis was conducted in accordance with the design criteria specified and included extensive use of computer-aided analytical methods to screen the candidate concepts and select the most promising concepts for the in-depth structural analysis.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-132575-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Arrow-wing supersonic cruise aircraft structural design concepts evaluation. Volume 4: Sections 15 through 21 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The analyses performed to provide structural mass estimates for the arrow wing supersonic cruise aircraft are presented. To realize the full potential for structural mass reduction, a spectrum of approaches for the wing and fuselage primary structure design were investigated. The objective was: (1) to assess the relative merits of various structural arrangements, concepts, and materials; (2) to select the structural approach best suited for the Mach 2.7 environment; and (3) to provide construction details and structural mass estimates based on in-depth structural design studies. Production costs, propulsion-airframe integration, and advanced technology assessment are included.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-132575-4
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Arrow-wing supersonic cruise aircraft structural design concepts evaluation. Volume 2: Sections 7 through 11 (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The materials and advanced producibility methods that offer potential structural mass savings in the design of the primary structure for a supersonic cruise aircraft are identified and reported. A summary of the materials and fabrication techniques selected for this analytical effort is presented. Both metallic and composite material systems were selected for application to a near-term start-of-design technology aircraft. Selective reinforcement of the basic metallic structure was considered as the appropriate level of composite application for the near-term design.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-132575-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Identifying and analyzing methods for reducing the energy consumption of helicopters (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results are presented of a study to identify those helicopter technology areas which would result in the largest energy (or fuel) savings when applied to large tandem (100 passenger) civil helicopters in the 1985 time frame. Baseline aircraft using 1975 technology in the areas of powerplant, rotor efficiency, parasite drag and structure were sized to a very short haul mission of 100 N.M. and a short haul mission of 200 N.M. A systematic parametric analysis was then conducted to assess the impact of technology improvements. Projections of the technology levels that could be obtained in the 1985 time frame were made and the resources estimated to achieve them. Based on these data, the highest payoff (lowest energy) helicopter technologies are identified.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144953 , D210-11007-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Study of fuel systems for LH2-fueled subsonic transport aircraft, volume 2 (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: For abstract, see N78-31085.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-145369-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Study of fuel systems for LH2-fueled subsonic transport aircraft, volume 1 (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Several engine concepts examined to determine a preferred design which most effectively exploits the characteristics of hydrogen fuel in aircraft tanks received major emphasis. Many candidate designs of tank structure and cryogenic insulation systems were evaluated. Designs of all major elements of the aircraft fuel system including pumps, lines, valves, regulators, and heat exchangers received attention. Selected designs of boost pumps to be mounted in the LH2 tanks, and of a high pressure pump to be mounted on the engine were defined. A final design of LH2-fueled transport aircraft was established which incorporates a preferred design of fuel system. That aircraft was then compared with a conventionally fueled counterpart designed to equivalent technology standards.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-145369-VOL-1 , LR-28384-VOL-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Identifying and analyzing methods for reducing the energy consumption of helicopters (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Reductions in helicopter energy consumption can be accomplished through the use of advanced technology in the areas of powerplant design, improved rotor efficiency, reduced parasite drag, and reduced structural empty weight. Baseline helicopters incorporating technology were designed for a short range (200 n mi) and a very short haul (100 n mi) mission scenario. Parametric analyses were then conducted to determine the impact of technology improvement. Many of the parameters varied are interrelated. A summary of such interactions is presented, and some additional sensitivity values were added so that energy reduction and DOC as affected by the major technological factors or operational modes are clearly defined.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-144953A
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Research requirements for development of improved helicopter rotor efficiency (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The research requirements for developing an improved-efficiency rotor for a civil helicopter are documented. The various design parameters affecting the hover and cruise efficiency of a rotor are surveyed, and the parameters capable of producing the greatest potential improvement are identified. Research and development programs to achieve these improvements are defined, and estimated costs and schedules are presented. Interaction of the improved efficiency rotor with other technological goals for an advanced civil helicopter is noted, including its impact on engine noise, hover and cruise performance, one-engine-inoperative hover capability, and maintenance and reliability.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: NASA-CR-145117
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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