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  • Other Sources  (79)
  • Aircraft Design, Testing and Performance  (79)
  • 2005-2009  (51)
  • 1950-1954  (9)
  • 1945-1949  (19)
  • 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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    The Influence of Clocking Angle of the Projectile on the Simulated Impact Response of a Shuttle Leading Edge Wing Panel (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: An analytical study was conducted to determine the influence of clocking angle of a foam projectile impacting a space shuttle leading edge wing panel. Four simulations were performed using LS-DYNA. The leading edge panels are fabricated of multiple layers of reinforced carbon-carbon (RCC) material. The RCC material was represented using Mat 58, which is a material property that can be used for laminated composite fabrics. Simulations were performed of a rectangular-shaped foam block, weighing 0.23-lb., impacting RCC Panel 9 on the top surface. The material properties of the foam were input using Mat 83. The impact velocity was 1,000 ft/s along the Orbiter X-axis. In two models, the foam impacted on a corner, in one model the foam impacted the panel initially on the 2-in.-long edge, and in the last model the foam impacted the panel on the 7-in.- long edge. The simulation results are presented as contour plots of first principal infinitesimal strain and time history plots of contact force and internal and kinetic energy of the foam and RCC panel.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TM-2005-213538 , ARL-TR-3447 , L-19098
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    High Altitude Long Endurance Air Vehicle Analysis of Alternatives and Technology Requirements Development (2007)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The objective of this study was to develop a variety of High Altitude Long Endurance (HALE) Unmanned Aerial Vehicle (UAV) conceptual designs for two operationally useful missions (hurricane science and communications relay) and compare their performance and cost characteristics. Sixteen potential HALE UAV configurations were initially developed, including heavier-than-air (HTA) and lighter-than-air (LTA) concepts with both consumable fuel and solar regenerative (SR) propulsion systems. Through an Analysis of Alternatives (AoA) down select process, the two leading consumable fuel configurations (one each from the HTA and LTA alternatives) and an HTA SR configuration were selected for further analysis. Cost effectiveness analysis of the consumable fuel configurations revealed that simply maximizing vehicle endurance can lead to a sub-optimum system solution. An LTA concept with a hybrid propulsion system (solar arrays and a hydrogen-air proton exchange membrane fuel cell) was found to have the best mission performance; however, an HTA diesel-fueled wing-body-tail configuration emerged as the preferred consumable fuel concept because of the large size and technical risk of the LTA concept. The baseline missions could not be performed by even the best HTA SR concept. Mission and SR technology trade studies were conducted to enhance understanding of the potential capabilities of such a vehicle. With near-term technology SR-powered HTA vehicles are limited to operation in favorable solar conditions, such as the long days and short nights of summer at higher latitudes. Energy storage system specific energy and solar cell efficiency were found to be the key technology areas for enhancing HTA SR performance.
    Keywords: Aircraft Design, Testing and Performance
    Type: 45th AIAA Aerospace Sciences Meeting and Exhibit; Jan 08, 2007 - Jan 11, 2007; Reno, NV; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Effect of Impact Location on the Response of Shuttle Wing Leading Edge Panel 9 (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-11
    Description: The objective of this paper is to compare the results of several simulations performed to determine the worst-case location for a foam impact on the Space Shuttle wing leading edge. The simulations were performed using the commercial non-linear transient dynamic finite element code, LS-DYNA. These simulations represent the first in a series of parametric studies performed to support the selection of the worst-case impact scenario. Panel 9 was selected for this study to enable comparisons with previous simulations performed during the Columbia Accident Investigation. The projectile for this study is a 5.5-in cube of typical external tank foam weighing 0.23 lb. Seven locations spanning the panel surface were impacted with the foam cube. For each of these cases, the foam was traveling at 1000 ft/s directly aft, along the orbiter X-axis. Results compared from the parametric studies included strains, contact forces, and material energies for various simulations. The results show that the worst case impact location was on the top surface, near the apex.
    Keywords: Aircraft Design, Testing and Performance
    Type: NASA/TM-2005-213544 , ARL-TR-3426 , L-19088
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Note on the Effects of First-Order Aerodynamic Loads on Propeller Shaft Loads with Emphasis on Counterrotating Propellers (1954)
    In:  CASI
    Details
    Publication Date: 2019-07-10
    Description: An investigation of the 1XP excitation of inclined single-rotation propellers has indicated a new concept for determining propeller shaft forces and moments of an inclined propeller. This report presents preliminary results, in particular to the counterrotating propeller.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-A54C30
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Determination of Aircraft Antenna Loads Produced by Natural Icing Conditions (1948)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A flight investigation was made to determine the effect of distance flown in the icing region, antenna length, and antenna angle on the tension occurring in aircraft antennae while in regions of aircraft icing. The experimental antennas were of lengths ranging from 15 to 43 feet and were placed at angles of 0 deg to 64 deg with the airplane thrust axis. Distances up to 256 miles were flown in diverse icing conditions at true airspeeds from 157 to 214 miles per hour and pressure altitudes at which icing conditions were encountered. The results indicate that: The effect of ice formation on antenna tension increased with the angle of the antennas with the longitudinal axis of the airplane. The maximum tension for antennae having angles from 0 deg to 15 deg was 68 pounds, whereas the maximum tension for antennas having angles of 44 deg and 64 deg was 274 and 438 pounds, respectively.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-RM-E7H26a
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Correlation of Mixture Temperature Data Obtained from Bare Intake-manifold Thermocouples (1946)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A relatively simple equation has been found to express with fair accuracy, variation in manifold-charge temperature with charge in engine operating conditions. This equation and associated curves have been checked by multi cylinder-engine data, both test stand and flight, over a wide range of operating conditions. Average mixture temperatures, predicted by the equations of this report, agree reasonably well with results within the same range of carburetor-air temperatures from laboratories and test stands other than the NACA.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-WR-E-273 , NACA-MR-E5L03
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    G2 Flywheel Module Operated at 41,000 rpm (2005)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: NASA Glenn Research Center s Flywheel Development Team designed, built, and successfully operated the new G2 flywheel to 41,000 rpm on September 2, 2004. This work was supported by the Aerospace Flywheel Technology Program--a NASA Office of Aerospace Technology ETC Program funded by the Energetics Project. The work was performed by a team of civil servants, contractors, and grantees managed by Glenn s Electrical Systems Development Branch, Structural Mechanics and Dynamics Branch, and Space Power & Propulsion Test Engineering Branch. The G2 flywheel was designed to be a low-cost modular testbed for flywheel system integration and component demonstrations.
    Keywords: Aircraft Design, Testing and Performance
    Type: Research and Technology 2004; NASA/TM-2005-213419
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Change Detection Experiments Using Low Cost UAVs (2005)
    In:  CASI
    Details
    Publication Date: 2019-07-27
    Description: This paper presents the progress in the development of a low-cost change-detection system. This system is being developed to provide users with the ability to use a low-cost unmanned aerial vehicle (UAV) and image processing system that can detect changes in specific fixed ground locations using video provided by an autonomous UAV. The results of field experiments conducted with the US Army at Ft. A.P.Hill are presented.
    Keywords: Aircraft Design, Testing and Performance
    Type: Infotech@Aerospace; 26-29 Sept. 2005; Arlington, VA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    On the Sound Field of a Rotating Propeller (1948)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: The sound field of a rotating propeller is teated theoretically on the basis of aerodynamic principles. For the lower harmonics, the directional characteristics and the radiated sound energy are determined and are in conformity with existing experimental results.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-TM-1195 , Physikalische Zeitschrit der Sowjetinion: Physical magazine of the Soviet Union volume 9 number 1; 9; 1; 57-71
    Format: application/pdf
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