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  • AERODYNAMICS  (25)
  • Electronics and Electrical Engineering  (13)
  • 2000-2004  (13)
  • 1980-1984  (19)
  • 1975-1979  (6)
  • 1
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    An exploratory study of area-efficient vortex flap concepts (1983)
    In:  Other Sources
    Details
    Publication Date: 2011-08-18
    Description: The potential of planform modification and hinge-line relocation to improve the thrust efficiency of vortex flaps was experimentally investigated on a 60-deg cropped delta wing model. Spanwise segmentation of the flap, together with chord-tailoring of the segments, allowed the vortex to be maintained on the outboard flap surfaces to higher angles of attack. In addition, location of the flap hinge aft of and underneath the wing leading edge generated substantial thrust from the vortex suction acting on the leading-edge lower surface. A combination of these beneficial effects allowed the flap/wing area to be reduced from 11.4 percent of the continuous flap to 6.3 percent of segmented flap, essentially without detriment to the incremental lift-to-drag ratio due to flap addition in the lift coefficient range 0.5-0.7 based on the basic wing area.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 20; 1062-106
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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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
  • 3
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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
  • 4
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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
  • 5
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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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  • 6
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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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  • 7
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    Vortical flow management for improved configuration aerodynamics: Recent experiences (1983)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: Recent progress in vortex-control applications for alleviating the adverse consequences of three dimensional separation and vortical interactions on slender body/swept wing configurations is reported. Examples include helical separation trip to alleviate the side force due to forebody vortex asymmetry; hinged strakes to avoid vortex breakdown effects; compartmentation of swept leading edge separation to delay the pitch-up instability; under wing vortex trip and vortex trip and vortex flaps for drag reduction at high lift; and an apex-flap trimmer to fully utilize the lift capability of trailing-edge flaps for take off and landing of delta wings. Experimental results on generic wind-tunnel models are presented to illustrate the vortex-management concepts involved and to indicate their potential for enhancing the subsonic aerodynamics of supersonic-cruise type vehicles.
    Keywords: AERODYNAMICS
    Type: AGARD Aerodyn. of Vortical Type Flows in Three Dimensions; 14 p
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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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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  • 9
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    Force and moment measurements on a 74 deg delta wing with an apex flap (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Results are presented of a subsonic experimental investigation of an apex flap concept on a 74 deg swept delta wing with trailing-edge flaps. The apex flap comprised approximately 6 percent of the wing area forward of a transverse hinge, allowing for upward and downward deflection angles from +40 deg to -20 deg. Upward deflection forces leading-edge vortex formation on the apex flap, resulting in an increased lift component on the apex area. The associated nose-up moment balances the nose-down moment due to trailing-edge flaps, resulting in sizeable increase in the trimmed lift coefficient particularly at low angles of attack. Nose-down apex deflection may be used to augment the pitch control for rapid recovery from high-alpha maneuvers. This report presents the balance data without analysis.
    Keywords: AERODYNAMICS
    Type: NASA-CR-166081 , NAS 1.26:166081
    Format: application/pdf
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  • 10
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    An analysis method for multi-component airfoils in separated flow (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The multi-component airfoil program (Langley-MCARF) for attached flow is modified to accept the free vortex sheet separation-flow model program (Analytical Methods, Inc.-CLMAX). The viscous effects are incorporated into the calculation by representing the boundary layer displacement thickness with an appropriate source distribution. The separation flow model incorporated into MCARF was applied to single component airfoils. Calculated pressure distributions for angles of attack up to the stall are in close agreement with experimental measurements. Even at higher angles of attack beyond the stall, correct trends of separation, decrease in lift coefficients, and increase in pitching moment coefficients are predicted.
    Keywords: AERODYNAMICS
    Type: NASA-CR-159300
    Format: application/pdf
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