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  • 1
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    Low-speed wind tunnel tests of two waverider configuration models (1995)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A definitive measurement of the low-speed flight characteristics of waverider-based aircraft is required to augment the overall design database for this important class of vehicles which have great potential for efficient high-speed flight. Two separate waverider-derived vehicles were tested; one in the 14- by 22-Foot Tunnel and the other in the 12-Foot Low-Speed Tunnel at Langley Research Center. These tests provided measurements of moments and forces about all three axes, control effectiveness, flow field characteristics and the effects of configuration changes. This paper will summarize the results of these tunnels and show the subsonic aerodynamic characteristics of the two configurations.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 95-6093 , ; 17 p.|AIAA, Aerospace Planes and Hypersonics Technologies Conference; Apr 03, 1995 - Apr 07, 1995; Chattanooga, TN; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Effects of Control-Response Characteristics on the Capability of Helicopter for Use as a Gun Platform (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An investigation with a variable-stability helicopter was undertaken to ascertain the steadiness and ability to "hold on" to the target of a helicopter employed as a gun platform. Simulated tasks were per formed under differing flight conditions with the control-response characteristics of the helicopter varied for each task. The simulated gun-platform mission included: Variations of headings with respect to wind, constant altitude and "swing around" to a wind heading of 0 deg, and increases in altitude while performing a swing around to a wind heading of 0 deg. The results showed that increases in control power and damping increased pilot ability to hold on to the target with fewer yawing oscillations and in a shorter time. The results also indicated that wind direction must be considered in accuracy assessment. Greatest accuracy throughout these tests was achieved by aiming upwind.
    Keywords: Aircraft Stability and Control
    Type: NASA-TN-D-464 , L-796
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Fast-Acting Valve (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: A fast-acting valve includes an annular valve seat that defines an annular valve orifice between the edges of the annular valve seat, an annular valve plug sized to cover the valve orifice when the valve is closed, and a valve-plug holder for moving the annular valve plug on and off the annular valve seat. The use of an annular orifice reduces the characteristic distance between the edges of the valve seat. Rather than this distance being equal to the diameter of the orifice, as it is for a conventional circular orifice, the characteristic distance equals the distance between the inner and outer radii (for a circular annulus). The reduced characteristic distance greatly reduces the gap required between the annular valve plug and the annular valve seat for the valve to be fully open, thereby greatly reducing the required stroke and corresponding speed and acceleration of the annular valve plug. The use of a valve-plug holder that is under independent control to move the annular valve plug between its open and closed positions is important for achieving controllable fast operation of the valve.
    Keywords: Mechanical Engineering
    Format: application/pdf
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  • 4
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    Airbreathing Hypersonic Vision-Operational-Vehicles Design Matrix (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents the status of the airbreathing hypersonic airplane and space-access vision-operational-vehicle design matrix, with emphasis on horizontal takeoff and landing systems being, studied at Langley, it reflects the synergies and issues, and indicates the thrust of the effort to resolve the design matrix including Mach 5 to 10 airplanes with global-reach potential, pop-up and dual-role transatmospheric vehicles and airbreathing launch systems. The convergence of several critical systems/technologies across the vehicle matrix is indicated. This is particularly true for the low speed propulsion system for large unassisted horizontal takeoff vehicles which favor turbines and/or perhaps pulse detonation engines that do not require LOX which imposes loading concerns and mission Flexibility restraints.
    Keywords: Aircraft Design, Testing and Performance
    Type: Rept-1999-01-5515 , 1999 World Aviation Conference; Oct 19, 1999 - Oct 21, 1999; San Francisco, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Design of a Hypersonic Waverider-Derived Airplane (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The paper describes the first assessment study of a waverider-derived Mach 5 aircraft design using fuselage integrated-underslung over/under turboramjets with endothermic fuel. The study is based on a tanker-to-tanker mission, which begins at Mach 0.8 and 30,000 feet, with the vehicle accelerating to Mach 12 at constant altitude and then to Mach 5 while climbing to about 90,000 feet. The paper describes the vehicle, the aerodynamic analysis, and the propulsion system and its installed performance, structure design, and analysis. The mission simulation was run using the CSOTAV code developed by the NASA Langley Research Center.
    Keywords: SPACECRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 93-0401 , E-7560 , ; 28 p.|AIAA, Aerospace Sciences Meeting and Exhibit; Jan 11, 1993 - Jan 14, 1993; Reno, NV; United States
    Format: text
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  • 6
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    Airbreathing Hypersonic Vision-Operational-Vehicles Design Matrix (1999)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: This paper presents the status of the airbreathing hypersonic airplane and space-access vision-operational-vehicle design matrix, with emphasis on horizontal takeoff and landing systems being studied at Langley; it reflects the synergies and issues, and indicates the thrust of the effort to resolve the design matrix including Mach 5 to 10 airplanes with global-reach potential, pop-up and dual-role transatmospheric vehicles and airbreathing launch systems. The convergence of several critical systems/technologies across the vehicle matrix is indicated. This is particularly true for the low speed propulsion system for large unassisted horizontal takeoff vehicles which favor turbines and/or perhaps pulse detonation engines that do not require LOX which imposes loading concerns and mission flexibility restraints.
    Keywords: Aircraft Design, Testing and Performance
    Type: Rept-1999-01-5515
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
    facet.materialart.
    Unknown
    Low-Speed Wind Tunnel Tests of Two Waverider Configuration Models (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A definitive measurement of the low-speed flight characteristics of waverider-based aircraft is required to augment the overall design database for this important class of vehicles which have great potential for efficient high-speed flight. Two separate waverider-derived vehicles were tested; one in the 14- by 22-Foot Tunnel and the other in the 12-Foot Low Speed Tunnel at Langley Research Center. These tests provided measurements of moments and forces about all three axes, control effectiveness, flow field characteristics and the effects of configuration changes. The results of these tunnel tests are summarized and the subsonic aerodynamic characteristics of the two configurations are shown.
    Keywords: Aerodynamics
    Type: NASA-TM-111795 , NAS 1.15:111795 , AIAA Paper 95-6093 , International Aerospace and Hypersonics Technologies; Apr 03, 1995 - Apr 07, 1995; Chattanooga, TN; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Design of Long-Endurance Unmanned Airplanes Incorporating Solar and Fuel Cell Propulsion (1984)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Preliminary performance analysis and conceptual design are described for a class of unmanned airplanes possessing multi-day endurance capability. A mixed-mode electric power system incorporates solar cells for daytime energy production and a non-regenerative H2-02 fuel cell to supply energy for night flight. The power system provides energy for all onboard systems, including propulsion., payload, and avionics. Excess solar energy is available during significant portions of the day, and may be used for climbing, maneuvering, or payload functions. By jettisoning fuel cell reactant product (water) during flight, vehicle endurance may be increased under certain conditions. Empirical structure sizing algorithms are combined with low-Reynolds number aerodynamics algorithms to estimate airplane size and geometry to meet prescribed mission requirements. Initial calculations for summertime, high-altitude flight (above 40,000 ft (12 km)) at moderate latitude (31 deg N) indicate that mission endurance of several days may be possible for configurations having wing loadings on the order of 0.9 to 1.3 lb/ft(exp 2). These aircraft tend to be somewhat smaller than solar-powered aircraft previously conceived for multi-month endurance utilizing regenerative fuel cell systems for night flight.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 84-1430 , AIAA/SAE/ASME 20th Joint Propulsion Conference; Jun 11, 1984 - Jun 13, 1984; Cincinnati, OH; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Summary of Flight-Test Results of the VZ-2 Tilt-Wing Aircraft (1962)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Flight-test information gained from a tilt-wing research aircraft tested at the Langley Research Center has shown that design problems exist in such fields as low-speed stability and control, handling qualities, and flow separation during transition. The control power in the near-hovering configuration was considered by the pilots to be inadequate in yaw, marginal in pitch, and excessive in roll. Solutions for some of the design problems are indicated; for example, the addition of a leading-edge droop to the wing in an attempt to delay flow separation resulted in such significantly improved handling qualities in the transition range that an additional descent capability of 1,100 feet per minute was obtained.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA-TN-D-989 , L-1574
    Format: application/pdf
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