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  • Electronics and Electrical Engineering  (13)
  • AERODYNAMICS  (6)
  • 2000-2004  (13)
  • 1975-1979  (6)
  • 1
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    Hypersonic incipient separation on delta wing with trailing-edge flap (1975)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: The paper reviews the experimental data on the incipient separation characteristics of planar delta wings of 75 degree sharp leading edges, with full-span trailing edge flap deflected into the windward flow. The local Reynolds number range for these investigations covered laminar, transitional and turbulent conditions. It is shown that, while turbulent boundary layer data correlates with two dimensional results, in the laminar and transitional cases, there is a nearly parallel shift to higher flap angles for incipient separation.
    Keywords: AERODYNAMICS
    Type: AIAA Journal; 13; Oct. 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Application of radial-splitters for improved wide-angle diffuser performance in a blowdown tunnel (1976)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Severe flow separation in the 15:1 area-ratio, 38 deg total angle conical diffuser preceding the settling-chamber of an intermittent blowdown wind tunnel was eliminated by the use of a novel radial-splitter arrangement. As a consequence, the operating life of settling-chamber screens was greatly extended and test-section flow steadiness improved, with no penalty in the tunnel running time.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft; 13; July 197
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Performance of Li-Ion Cells Under Battery Voltage Charge Control (2002)
    In:  CASI
    Details
    Publication Date: 2017-09-27
    Description: Li-ion cells manufactured by YTP, SAFT, and MSA have completed 6714, 6226, and 3441 cycles, respectively. An increase in the charge voltage limit was required in all cases to maintain the discharge voltage. SAFT and MSA cells were capable of cycling at -10 C and 0 C with an increase in the charge voltage limit, whereas Yardney cells could not be cycled. Reconditioning improved the discharge voltage of SAFT and MSA cells; it is important to note that the effect has been temporary as in Ni-H and Ni-Cd batteries. It was demonstrated that the charge operation with VT clamp at battery rather than at cell level is feasible. Continuation of testing depends on the health of the cells and on the funding situation.
    Keywords: Electronics and Electrical Engineering
    Type: The 2001 NASA Aerospace Battery Workshop; NASA/CP-2002-211466
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    NASA/GSFC Testing of Li-Ion Cells: Update (2001)
    In:  CASI
    Details
    Publication Date: 2017-09-27
    Description: This viewgraph paper presents a report on the ongoing testing of Lithium Ion (Li-Ion) cells. Characterizes cells according to capacity, self-discharge, and mid-discharge voltage. Determines the cycling performance of Li-Ion cells as batteries according to number of cycles, charge voltage, and temperature.
    Keywords: Electronics and Electrical Engineering
    Type: The 2000 NASA Aerospace Battery Workshop; NASA/CP-2001-210883
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Crane Cell Testing Support of Nasa/goddard Space Flight Center: an Update (2001)
    In:  CASI
    Details
    Publication Date: 2014-10-07
    Description: The objective of this paper is to verify the quality and reliability of aerospace battery cells and batteries for NASA flight programs, disseminate the data - to develop a plan for in-orbit battery management - to design a cell/battery for future NASA spacecraft and establish a cell test data base for rechargeable cell/batteries.
    Keywords: Electronics and Electrical Engineering
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    AEA Cell-Bypass-Switch Activation: An Update (2002)
    In:  CASI
    Details
    Publication Date: 2017-09-27
    Description: The objectives of this project included the following: (1) verify the performance of AEA cell bypass protection device (CBPD) under simulated EOS-Aqua/Aura flight hardware configuration; (2) assess the safety of the hardware under an inadvertent firing of CBPD switch, as well as the closing of CBPD; and (3) confirm that the mode of operation of CBPD switch is the formation of a continuous low impedance path (a homogeneous low melting point alloy). The nominal performance of AEA CBPD under flight operating conditions (vacuum except zero-G, and high impedance cell) has been demonstrated. There is no evidence of cell rupture or excessive heat production during or after CBPD switch activation under simulated high cell impedance (open-circuit cell failure mode). The formation of a continuous low impedance path (a homogeneous low melting point alloy) has been confirmed.
    Keywords: Electronics and Electrical Engineering
    Type: The 2001 NASA Aerospace Battery Workshop; NASA/CP-2002-211466
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    Side-force alleviation on slender, pointed forebodies at high angles of attack (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A new device was proposed for alleviating high angle-of-attack side force on slender, pointed forebodies. A symmetrical pair of separation strips in the form of helical ridges are applied to the forebody to disrupt the primary lee-side vortices and thereby avoid the instability that produces vortex asymmetry. Preliminary wind tunnel tests at Mach 0.3 and Reynolds no. 5,250,000 on a variety of forebody configurations and on a wing-body combination at angles of attack up to 56 degrees, demonstrated the effectiveness of the device.
    Keywords: AERODYNAMICS
    Type: NASA-CR-145361
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Study of Capacity and Voltage Degradation in Nickel-Hydrogen Cells (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The objective of this study is to understand the causes of the nickel hydrogen (NiH2) cell degradetion: storage, cycling, and reversal.
    Keywords: Electronics and Electrical Engineering
    Type: Space Power Workshop; Apr 19, 2004 - Apr 22, 2004; Manhattan Beach, CA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Effect of Handling, Storage and Cycling on Ni-H2 Cells: Second Plateau Phenomenon (2000)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A viewgraph presentation outlines the effects of handling, storing, and cycling of NiH2 cells, particularly the second plateau phenomenon. Details are given on the criteria for cell selection, cell history, the second plateau capacity at C/2 discharge, and cell reversal test conditions. Tables display a gas analysis and nickel precharge.
    Keywords: Electronics and Electrical Engineering
    Type: 2000 NASA Aerospace Battery Workshop; Nov 14, 2000 - Nov 16, 2000; Huntsville, AL; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Wind tunnel tests on a tail-less swept wing span-distributed cargo aircraft configuration (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The configuration consisted of a 30 deg -swept, untapered, untwisted wing utilizing a low-moment cambered airfoil of 20 percent streamwise thickness designed for low wave drag at M = 0.6, C sub L = 0.4. The tests covered a range of Mach numbers 0.3 to 0.725 and chord Reynolds number 1,100,000 to 2,040,000, angles of attack up to model buffet and sideslip angles + or - 4 deg. Configuration build up, wing pod filleting, airfoil modification and trailing edge control deflection effects were briefly investigated. Three wing tip vertical tail designs were also tested. Wing body filleting and a simple airfoil modification both produced increments to maximum lift/drag ratio. Addition of pods eliminated pitch instability of the basic wing. While the magnitude of these benefits probably was Reynolds number sensitive, they underline the potential for improving the aerodynamics of the present configuration. The cruise parameter (product of Mach number and lift/drag ratio) attained a maximum close to the airfoil design point. The configuration was found to be positively stable with normal control effectiveness about all three axes in the Mach number and C sub L range of interest.
    Keywords: AERODYNAMICS
    Type: NASA-TM-78767
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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