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  • Aircraft Design, Testing and Performance
  • 2010-2014  (29)
  • 2005-2009  (41)
  • 1975-1979  (1)
  • 1965-1969  (1)
  • 1950-1954  (5)
  • 1940-1944  (3)
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Years
Year
  • 1
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    Gen 2.0 Mixer/Ejector Nozzle Test at LSAF June 1995 to July 1996 (2005)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: Testing of the HSCT Generation 2.0 nozzle model hardware was conducted at the Boeing Low Speed Aeroacoustic Facility, LSAF. Concurrent measurements of noise and thrust were made at critical takeoff design conditions for a variety of mixer/ejector model hardware. Design variables such as suppressor area ratio, mixer area ratio, liner type and thickness, ejector length, lobe penetration, and mixer chute shape were tested. Parallel testing was conducted at G.E.'s Cell 41 acoustic free jet facility to augment the LSAF test. The results from the Gen 2.0 testing are being used to help shape the current nozzle baseline configuration and guide the efforts in the upcoming Generation 2.5 and 3.0 nozzle tests. The Gen 2.0 results have been included in the total airplane system studies conducted at MDC and Boeing to provide updated noise and thrust performance estimates.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/CR-2005-213334 , E-14804
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    In-Flight Boundary-Layer Transition of a Large Flat Plate at Supersonic Speeds (2012)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: A flight experiment was conducted to investigate the pressure distribution, local-flow conditions, and boundary-layer transition characteristics on a large flat plate in flight at supersonic speeds up to Mach 2.00. The tests used a NASA testbed aircraft with a bottom centerline mounted test fixture. The primary objective of the test was to characterize the local flow field in preparation for future tests of a high Reynolds number natural laminar flow test article. A second objective was to determine the boundary-layer transition characteristics on the flat plate and the effectiveness of using a simplified surface coating. Boundary-layer transition was captured in both analog and digital formats using an onboard infrared imaging system. Surface pressures were measured on the surface of the flat plate. Flow field measurements near the leading edge of the test fixture revealed the local flow characteristics including downwash, sidewash, and local Mach number. Results also indicated that the simplified surface coating did not provide sufficient insulation from the metallic structure, which likely had a substantial effect on boundary-layer transition compared with that of an adiabatic surface. Cold wall conditions were predominant during the acceleration to maximum Mach number, and warm wall conditions were evident during the subsequent deceleration.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TM-2012-216021 , DFRC-E-DAA-TN5282
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Large Engine Technology Program. Task 21: Rich Burn Liner for Near Term Experimental Evaluations (2005)
    In:  CASI
    Details
    Publication Date: 2019-08-13
    Description: The objective of the task reported herein, which was conducted as part of the NASA sponsored Large Engine Technology program, was to define and evaluate a near-term rich-zone liner construction based on currently available materials and fabrication processes for a Rich-Quench-Lean combustor. This liner must be capable of operation at the temperatures and pressures of simulated HSCT flight conditions but only needs sufficient durability for limited duration testing in combustor rigs and demonstrator engines in the near future. This must be achieved at realistic cooling airflow rates since the approach must not compromise the emissions, performance, and operability of the test combustors, relative to the product engine goals. The effort was initiated with an analytical screening of three different liner construction concepts. These included a full cylinder metallic liner and one with multiple segments of monolithic ceramic, both of which incorporated convective cooling on the external surface using combustor airflow that bypassed the rich zone. The third approach was a metallic platelet construction with internal convective cooling. These three metal liner/jacket combinations were tested in a modified version of an existing Rich-Quench-Lean combustor rig to obtain data for heat transfer model refinement and durability verification.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/CR-2005-213136 , E-14650
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    INITIAL ASSESSMENT OF SURFACE PRESSURE CHARACTERISTICS OF TWO ROTARY WING UAV DESIGNS (2006)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents results of an experimental investigation of two rotary-wing UAV designs. The primary goal of the investigation was to provide a set of interactional aerodynamic data for an emerging class of rotorcraft. The present paper provides an overview of the test and an introduction to the test articles, and instrumentation. Sample data in the form of fixed system pressure coefficient response to changes in configuration attitude and flight condition for both rotor off and on conditions are presented. The presence of the rotor is seen to greatly affect the magnitude of the response. Pressure coefficients were measured using both conventional pressure taps and via pressure sensitive paint. Comparisons between the two methods are presented and demonstrate that the pressure sensitive paint is a promising method; however, further work on the technique is required.
    Keywords: Aircraft Design, Testing and Performance
    Type: AHS International 62nd Annual Forum and Technology Display; May 09, 2006 - May 11, 2006; Phoenix, AZ; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Bias Momentum Sizing for Hovering Dual-Spin Platforms (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An atmospheric flight vehicle in hover is typically controlled by varying its thrust vector. Achieving both levitation and control with the propulsion system places considerable demands on it for agility and precision, particularly if the vehicle is statically unstable, or nearly so. These demands can be relaxed by introducing an appropriately sized angular momentum bias about the vehicle's yaw axis, thus providing an additional margin of attitude stability about the roll and pitch axes. This paper describes an approach for specifying the appropriate size of such angular momentum bias, based on the vehicle s physical parameters and its disturbance environment. It also describes several simplifications that provide a more physical and intuitive understanding of the dynamics. This will enhance the possibility of practically applying this technology to a flying vehicle.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2005-5973 , AIAA Guidance, Navigation, and Control Conference and Exhibit; Aug 15, 2005 - Aug 18, 2005; San Francisco, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    CMG-Augmented Control of a Hovering VTOL Platform (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper describes how Control Moment Gyroscopes (CMGs) can be used for stability augmentation to a thrust vectoring system for a generic Vertical Take-Off and Landing platform. The response characteristics of the platform which uses only thrust vectoring and a second configuration which includes a single-gimbal CMG array are simulated and compared for hovering flight while subject to severe air turbulence. Simulation results demonstrate the effectiveness of a CMG array in its ability to significantly reduce the agility requirement on the thrust vectoring system. Albeit simplifying physical assumptions on a generic CMG configuration, the numerical results also suggest that reasonably sized CMGs will likely be sufficient for a small hovering vehicle.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA Paper 2007-6458 , AIAA Guidance, Navigation, and Control Conference and Exhibit; Aug 20, 2007 - Aug 23, 2007; Hilton Head, SC; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Plans and Status of Wind-Tunnel Testing Employing an Aeroservoelastic Semispan Model (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents the research objectives, summarizes the pre-wind-tunnel-test experimental results to date, summarizes the analytical predictions to date, and outlines the wind-tunnel-test plans for an aeroservoelastic semispan wind-tunnel model. The model is referred to as the Supersonic Semispan Transport (S4T) Active Controls Testbed (ACT) and is based on a supersonic cruise configuration. The model has three hydraulically-actuated surfaces (all-movable horizontal tail, all-movable ride control vane, and aileron) for active controls. The model is instrumented with accelerometers, unsteady pressure transducers, and strain gages and will be mounted on a 5-component sidewall balance. The model will be tested twice in the Langley Transonic Dynamics Tunnel (TDT). The first entry will be an "open-loop" model-characterization test; the second entry will be a "closed-loop" test during which active flutter suppression, gust load alleviation and ride quality control experiments will be conducted.
    Keywords: Aircraft Design, Testing and Performance
    Type: AIAA 2007-1770 , 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference; Apr 23, 2007 - Apr 26, 2007; Waikiki, HI; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Experimental Investigation of Spreading Characteristics of Choked Jets Expanding into Quiescent Air (1950)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: Investigations have been conducted to determine by means of total-pressure surveys the boundaries of single and twin jets discharging through convergent nozzles into quiescent air. The jet boundaries for the region from the nozzle outlets to a station 6 nozzle diameters downstream are presented for nozzle pressure ratios ranging from 2.5 t o 16.0 and for twin-Jet nozzle center-line spacings ranging from 1.42 to 2.50 nozzle diameters. The effects of these parameters on the interaction of twin Jets are discussed. In order to ascertain the utility of the results for other than the test conditions, the effects of jet temperature, Reynolds number, and humidity on the pressure boundaries have been briefly investigated. The result indicate that for a jet of 2.6 the pressure boundaries are slightly smaller than those of corresponding unheated jets and that the effects of Reynolds number and humidity are negligible.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E50E03a
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    N+3 Aircraft Concept Designs and Trade Studies (2010)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Appendices A to F present the theory behind the TASOPT methodology and code. Appendix A describes the bulk of the formulation, while Appendices B to F develop the major sub-models for the engine, fuselage drag, BLI accounting, etc.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/CR-2010-216794/VOL2 , E-17419-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    N+3 Aircraft Concept Designs and Trade Studies (2010)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: MIT, Aerodyne Research, Aurora Flight Sciences, and Pratt & Whitney have collaborated to address NASA s desire to pursue revolutionary conceptual designs for a subsonic commercial transport that could enter service in the 2035 timeframe. The MIT team brings together multidisciplinary expertise and cutting-edge technologies to determine, in a rigorous and objective manner, the potential for improvements in noise, emissions, and performance for subsonic fixed wing transport aircraft. The collaboration incorporates assessment of the trade space in aerodynamics, propulsion, operations, and structures to ensure that the full spectrum of improvements is identified. Although the analysis focuses on these key areas, the team has taken a system-level approach to find the integrated solutions that offer the best balance in performance enhancements. Based on the trade space analyses and system-level assessment, two aircraft have been identified and carried through conceptual design to show both the in-depth engineering that underpins the benefits envisioned and also the technology paths that need to be followed to enable, within the next 25 years, the development of aircraft three generations ahead in capabilities from those flying today.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/CR-2010-216794/VOL1 , E-17419-1
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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