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  • 1
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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
  • 2
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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
  • 3
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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
  • 4
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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
  • 5
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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
  • 6
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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
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 7
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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
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 8
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    Shake Test Results and Dynamic Calibration Efforts for the Large Rotor Test Apparatus (2014)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Prior to the full-scale wind tunnel test of the UH-60A Airloads rotor, a shake test was completed on the Large Rotor Test Apparatus. The goal of the shake test was to characterize the oscillatory response of the test rig and provide a dynamic calibration of the balance to accurately measure vibratory hub loads. This paper provides a summary of the shake test results, including balance, shaft bending gauge, and accelerometer measurements. Sensitivity to hub mass and angle of attack were investigated during the shake test. Hub mass was found to have an important impact on the vibratory forces and moments measured at the balance, especially near the UH-60A 4/rev frequency. Comparisons were made between the accelerometer data and an existing finite-element model, showing agreement on mode shapes, but not on natural frequencies. Finally, the results of a simple dynamic calibration are presented, showing the effects of changes in hub mass. The results show that the shake test data can be used to correct in-plane loads measurements up to 10 Hz and normal loads up to 30 Hz.
    Keywords: Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN12524 , Decennial AHS Aeromechanics Specialists'' Conference; Jan 22, 2014 - Jan 24, 2014; San Francisco, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Environmentally Friendly Rotorcraft Concepts: 2011-2014 (2013)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Motivation: Greenhouse gas concentrations have increased well beyond their pre-industrial levels due to human activities; Aircraft emissions are becoming regulated in industrialized nations, so future rotorcraft will need to be designed for minimal environmental impact. Objectives: Determine suitable metrics to measure environmental impact of rotorcraft, focusing first on air pollution; Integrate performance metrics with rotorcraft design codes; Generate rotorcraft designs with minimal environmental impact. Outcomes: Obtain an understanding of how targeting reduced emissions affects the rotorcraft design process; Advance the capability of existing rotorcraft design tools to include environmental performance metrics. Tools: Evaluation and predesign - NDARC (NASA Design and Analysis of Rotorcraft) and CREATION (Concepts of Rotorcraft Enhanced Assessment Through Integrated Optimization Network); Flight simulation - CAMRAD II (Comprehensive Analytical Model of Rotorcraft Aerodynamics and Dynamics) and HOST (Helicopter Overall Simulation Tool).
    Keywords: Aircraft Design, Testing and Performance
    Type: ARC-E-DAA-TN9508 , US/France MoA Helicopter Aeromechanics Semiannual Meeting; May 28, 2013 - May 29, 2013; Moffet Field, CA; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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