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  • Aircraft Design, Testing and Performance  (16)
  • 2010-2014  (9)
  • 2000-2004  (5)
  • 1945-1949  (1)
  • 1940-1944
  • 1935-1939  (1)
  • 1
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    Flow and Noise Control: Toward a Closer Linkage (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Motivated by growing demands for aircraft noise reduction and for revolutionary new aerovehicle concepts, the late twentieth century witnessed the beginning of a shift from single-discipline research, toward an increased emphasis on harnessing the potential of flow and noise control as implemented in a more fully integrated, multidisciplinary framework. At the same time, technologies for developing radically new aerovehicles, which promise quantum leap benefits in cost, safety and performance benefits with environmental friendliness, have appeared on the horizon. Transitioning new technologies to commercial applications will also require coupling further advances in traditional areas of aeronautics with intelligent exploitation of nontraditional and interdisciplinary technologies. Physics-based modeling and simulation are crucial enabling capabilities for synergistic linkage of flow and noise control. In these very fundamental ways, flow and noise control are being driven to be more closely linked during the early design phases of a vehicle concept for optimal and mutual noise and performance benefits.
    Keywords: Aircraft Design, Testing and Performance
    Type: 23rd International Council of the Aeronautical Sciences; Sep 08, 2002 - Sep 13, 2002; Toronto; Canada
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Exploration of Configuration Options for a Large Civil Compound Helicopter (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Multiple compound helicopter configurations are designed using a combination of rotorcraft sizing and comprehensive analysis codes. Results from both the conceptual design phase and rotor comprehensive analysis are presented. The designs are evaluated for their suitability to a short-to-medium-haul civil transport mission carrying a payload of 90 passengers. Multiple metrics are used to determine the best configuration, with heavy emphasis placed on minimizing fuel burn.
    Keywords: Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN6212 , 69th American Helicopter Society Annual Forum; May 21, 2013 - May 23, 2013; Phoenix, AZ; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Application of Climate Impact Metrics to Civil Tiltrotor Design (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Multiple metrics are applied to the design of a large civil tiltrotor, integrating minimum cost and minimum environmental impact. The design mission is passenger transport with similar range and capacity to a regional jet. Separate aircraft designs are generated for minimum empty weight, fuel burn, and environmental impact. A metric specifically developed for the design of aircraft is employed to evaluate emissions. The designs are generated using the NDARC rotorcraft sizing code, and rotor analysis is performed with the CAMRAD II aeromechanics code. Design and mission parameters such as wing loading, disk loading, and cruise altitude are varied to minimize both cost and environmental impact metrics. This paper presents the results of these parametric sweeps as well as the final aircraft designs.
    Keywords: Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN7037 , AIAA Aerospace Sciences Meeting; Jan 07, 2013 - Jan 10, 2013; Grapevine, TX; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Aeroacoustic and Performance Simulations of a Test Scale Open Rotor (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper explores a comparison between experimental data and numerical simulations of the historical baseline F31/A31 open rotor geometry. The experimental data were obtained at the NASA Glenn Research Center s Aeroacoustic facility and include performance and noise information for a variety of flow speeds (matching take-off and cruise). The numerical simulations provide both performance and aeroacoustic results using the NUMECA s Fine-Turbo analysis code. A non-linear harmonic method is used to capture the rotor/rotor interaction.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TM-2013-217707 , AIAA Paper-2012-3823 , E-18631 , 48th Joint Propulsion Conference and Exhibit; Jul 30, 2012 - Aug 01, 2012; Atlanta, GA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Conceptual Design and Performance Analysis for a Large Civil Compound Helicopter (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A conceptual design study of a large civil compound helicopter is presented. The objective is to determine how a compound helicopter performs when compared to both a conventional helicopter and a tiltrotor using a design mission that is shorter than optimal for a tiltrotor and longer than optimal for a helicopter. The designs are generated and analyzed using conceptual design software and are further evaluated with a comprehensive rotorcraft analysis code. Multiple metrics are used to determine the suitability of each design for the given mission. Plots of various trade studies and parameter sweeps as well as comprehensive analysis results are presented. The results suggest that the compound helicopter examined for this study would not be competitive with a tiltrotor or conventional helicopter, but multiple possibilities are identified for improving the performance of the compound helicopter in future research.
    Keywords: Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN4612 , AHS Future Vertical Lift Aircraft Design Conference; Jan 18, 2012 - Jan 20, 2012; San Francisco, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Jet engine nozzle exit configurations, including projections oriented relative to pylons, and associated systems and methods (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections extending in an aft direction. Aft portions of individual neighboring projections are spaced apart from each other by a gap, and a geometric feature of the multiple can change in a monotonic manner along at least a portion of the perimeter. Projections near a support pylon and/or associated heat shield can have particular configurations, including greater flow immersion than other projections.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Avionic Pictorial Tunnel-/Pathway-/Highway-In-The-Sky Workshops (2003)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: In 1994-96, Langley Research Center held a series of interactive workshops investigating highway-in-the-sky concepts, which enable precise flight path control. These workshops brought together government and industry display designers and pilots to discuss and fly various concepts in an iterative manner. The primary emphasis of the first workshops was the utility and usability of pathways and the pros and cons of various features available. The final workshops were focused on the specific applications to the eXternal Visibility System (XVS) of the NASA High-speed Research Program, which was concerned with replacement of the forward windows in a High-speed Civil Transport with electronic displays and high resolution video cameras to enable a "No-Droop" configuration. The primary concerns in the XVS application were the prevention of display clutter and obscuration of hazards, as the camera image was the primary means of traffic separation in clear visibility conditions. These concerns were not so prominent in the first workshops, which assumed a Synthetic Vision System application in which hazard locations are known and obscuration is handled easily. The resulting consensus concept has been used since in simulation and flight test activities of many Government programs. and other concepts have been influenced by the workshop discussions.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/CP-2003-212164 , L-18270 , NAS 1.55:212164 , Avionic Pictorial Tunnel-/Pathway-/Highway-In-The-Sky Workshop #3; Mar 21, 1995 - Mar 22, 1995; Hampton, VA; United States|Avionic Pictorial Tunnel-/Pathway-/Highway-In-The-Sky Workshop #2; Sep 20, 1994 - Sep 22, 1994; Hampton, VA; United States|Avionic Pictorial Tunnel-/Pathway-/Highway-In-The-Sky Workshop #4; Sep 04, 1996 - Sep 05, 1996; Hampton, VA; United States|Avionic Pictorial Tunnel-/Pathway-/Highway-In-The-Sky Workshop #1; Apr 25, 1994 - Apr 27, 1994; Hampton, VA; United States
    Format: application/pdf
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  • 8
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    Blended Cutout Flap for Reduction of Jet-Flap Interaction Noise (2014)
    In:  CASI
    Details
    Publication Date: 2019-08-28
    Description: An aircraft system includes a wing and a trailing edge device coupled to the wing. The trailing edge device is movable relative to the wing, and includes a leading edge and a trailing edge having a center flap portion and a plurality of outer edge portions integrally combined with the center flap portion such that the center flap portion is shorter in width than that of outer edge portions.
    Keywords: Aircraft Design, Testing and Performance
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    In-Flight Vibration Environment of the NASA F-15B Flight Test Fixture (2002)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: Flight vibration data are analyzed for the NASA F-15B/Flight Test Fixture II test bed. Understanding the in-flight vibration environment benefits design and integration of experiments on the test bed. The power spectral density (PSD) of accelerometer flight data is analyzed to quantify the in-flight vibration environment from a frequency of 15 Hz to 1325 Hz. These accelerometer data are analyzed for typical flight conditions and maneuvers. The vibration data are compared to flight-qualification random vibration test standards. The PSD levels in the lateral axis generally are greater than in the longitudinal and vertical axes and decrease with increasing frequency. At frequencies less than approximately 40 Hz, the highest PSD levels occur during takeoff and landing. Peaks in the PSD data for the test fixture occur at approximately 65, 85, 105-110, 200, 500, and 1000 Hz. The pitch-pulse and 2-g turn maneuvers produce PSD peaks at 115 Hz. For cruise conditions, the PSD level of the 85-Hz peak is greatest for transonic flight at Mach 0.9. From 400 Hz to 1325 Hz, the takeoff phase has the highest random vibration levels. The flight-measured vibration levels generally are substantially lower than the random vibration test curve.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TM-2002-210719 , H-2468 , NAS 1.15:210719
    Format: application/pdf
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  • 10
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    Application of Climate Impact Metrics to Rotorcraft Design (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Multiple metrics are applied to the design of large civil rotorcraft, integrating minimum cost and minimum environmental impact. The design mission is passenger transport with similar range and capacity to a regional jet. Separate aircraft designs are generated for minimum empty weight, fuel burn, and environmental impact. A metric specifically developed for the design of aircraft is employed to evaluate emissions. The designs are generated using the NDARC rotorcraft sizing code, and rotor analysis is performed with the CAMRAD II aeromechanics code. Design and mission parameters such as wing loading, disk loading, and cruise altitude are varied to minimize both cost and environmental impact metrics. This paper presents the results of these parametric sweeps as well as the final aircraft designs.
    Keywords: Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN5356 , AIAA Aerospace Sciences Meeting; Jan 07, 2013 - Jan 10, 2013; Fort Worth, TX; Albania
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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