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  • AERODYNAMICS  (7)
  • Amino acid sequence
  • 2000-2004
  • 1980-1984  (8)
  • 1975-1979
  • 1983  (5)
  • 1980  (3)
  • 1
    Electronic Resource
    Electronic Resource
    The structure of bovine rhodopsin (1983)
    Springer
    European biophysics journal 9 (1983), S. 235-244 
    Details
    ISSN: 1432-1017
    Keywords: Rhodopsin ; Amino acid sequence ; Secondary structure ; Topography ; Disk membrane
    Source: Springer Online Journal Archives 1860-2000
    Topics: Biology , Physics
    Notes: Abstract We have isolated 16 peptides from a cyanogen bromide digest of rhodopsin. These cyanogen bromide peptides account for the complete composition of the protein. Methionine-containing peptides from other chemical and enzymatic digests of rhodopsin have allowed us to place the cyanogen bromide peptides in order, yielding the sequence of the protein. We have completed the sequence of most of the cyanogen bromide peptides. This information, in conjunction with that from other laboratories, forms the basis for our prediction of the secondary structure of the protein and how it may be arranged in the disk membrane.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1007/BF00535659
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    Paper (German National Licenses)
    Fulltext
  • 2
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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
  • 3
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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
  • 4
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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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    NASA TECHNICAL REPORTS
  • 5
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    Aerodynamic side-force alleviator means (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An apparatus for alleviating high angle of attack side force on slender pointed cylindrical forebodies such as fighter aircraft, missiles and the like is described. A symmetrical pair of helical separation trips was employed to disrupt the leeside vortices normally attained. The symmetrical pair of trips starts at either a common point or at space points on the upper surface of the forebody and extends along separate helical paths along the circumference of the forebody.
    Keywords: AERODYNAMICS
    Format: application/pdf
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  • 6
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    Flat-plate drag measurements with vortex generators in turbulent boundary layer (1983)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Direct drag measurements were obtained on a flat plate with a spanwise row of vortex generators near the leading edge, to produce an array of stream wise vortices within the approaching turbulent boundary layer. The object was to explore the possibility of modifying the large scale structure of the boundary layer through embedded longitudinal vortices with a view to obtaining a reduction in wall shear. Both obstacle and vane type vortex generators were tested at free stream velocities 40 ft/sec to 130 ft/sec corresponding to plate length Reynolds no. 0.3 million to 0.8 million with a nominal boundary layer thickness of approximately 0.6 in. at the leading edge. A few vortex generator configurations were tested both on and off the plate to measure the total drag as well as the plate drag alone. The obstacle type devices reduced the plate drag, indicating that the wake momentum defect predominated even in the presence of streamwise vortices. The vane type vortex generators however always increased the plate drag.
    Keywords: AERODYNAMICS
    Type: NASA-CR-172125 , NAS 1.26:172125 , VIRA-83-01
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Segmented vortex flaps (1983)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Segmented vortex flaps were suggested as a means of delaying the vortex spill-over causing thrust loss over the outboard region of single-panel flaps. Also proposed was hinge-line setback for exploiting leading-edge suction in conjunction with vortex flaps to improve the overall thrust per unit flap area. These two concepts in combination were tested on a 60-deg cropped delta wing model. Significant improvement in flap efficiency was indicated by a reduction of the flap/wing area from 11.4% of single-panel flap to 6.3% of a two segment delta flap design, with no lift/drag penalty at lift coefficients between 0.5 and 0.7. The more efficient vortex flap arrangement of this study should benefit the performance attainable with flaps of given area on wings of moderate leading-edge sweep.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 83-0424 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 10, 1983 - Jan 13, 1983; Reno, NV
    Format: text
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  • 8
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    Leading-edge 'Vortex Flaps' for enhanced subsonic aerodynamics of slender wings (1980)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The 'Vortex Flap' is a novel concept aimed at reducing the lift-dependent drag due to leading-edge flow separation on highly swept, slender wings at high angles of attack. The suction effect of coiled vortices generated via controlled separation over leading-edge flap surfaces is utilized to produce an aerodynamic thrust component. This principle was verified through wind-tunnel experiments on 74-deg and 60-deg delta wings and a supersonic-cruise slender wing aircraft configuration. Adaptation of the vortex-flap for augmentation of roll-control on the 74-deg delta at high angles of attack also was demonstrated. Selected results are presented in this paper to indicate the potential of the vortex flap concept to enhance the low-speed performance, stability and control of slender wing aircraft.
    Keywords: AERODYNAMICS
    Type: International Council of the Aeronautical Sciences, Congress; Oct 12, 1980 - Oct 17, 1980; Munich; Germany
    Format: text
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