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    {
      "id": "652",
      "score": 11.3263855,
      "title": "pressure distribution on two dimensional wings near the ground .",
      "abstract": "pressure distribution on two dimensional wings near the ground . a simple method of calculating the pressure distribution in incompressible flow on two-dimensional aerofoils of arbitrary section at moderate distances from the ground is developed . comparisons with an /exact/ potential flow solution, and with measurements on a 10 thick aerofoil of rae.101 section, provide a satisfactory verification of the adequacy of the method ,. but it is shown that it is necessary to take account of the boundary layer on the aerofoil in the calculations .",
      "source": "reconstructed-from-retrieval-pools-gen017"
    },
    {
      "id": "1092",
      "score": 10.557207,
      "title": "wing-nacelle-propeller interference for wings of various spans . force and pressure distribution tests .",
      "abstract": "wing-nacelle-propeller interference for wings of various spans . force and pressure distribution tests . an experimental investigation was made in the n. a. c. a. full-scale wind tunnel to determine the effect of wing span on nacelle-propeller characteristics and, reciprocally, the lateral extent of nacelle and propeller influence on a monoplane wing . the results provide a check on the validity of the previous research on nacelles and propellers with 15-foot-span wings tested in the the scale propeller and the n. a. c. a. cowling used in the former researches were tested in three typical tractor locations with respect to a thick wing of 5-foot chord and 30-foot span . the span was progressively reduced to 25,20, and 15 feet and the same characteristics were measured in each case . the efficiency factors--propulsive efficiency, nacelle drag efficiency, and net efficiency--were obtained for each wing length by means of force tests and the values are compared to determine the effect of span . pressure-distribution measurements show the lateral extent of the nacelle interference and the propeller-slipstream effect on the span loading for the various conditions . complete polar curves and curves showing the variation of nacelle drag with lift coefficient are also included . force and pressure-distribution tests concur in indicating that, for engineering purposes, the influence of a nacelle and of a propeller, in a usual combination, may be considered to extend laterally on a wing the same maximum distance, or about five nacelle diameters or two propeller diameters outboard of their common axes . all important effects of scale nacelle-propeller combinations may be measured within practical limits of accuracy by tests of a 15-foot-span wing .",
      "source": "reconstructed-from-retrieval-pools-gen017"
    },
    {
      "id": "250",
      "score": 10.253754,
      "title": "pressure distributions at zero lift for delta wings with rhombic cross sections .",
      "abstract": "pressure distributions at zero lift for delta wings with rhombic cross sections . the linearised theory of thin wings is used to calculate pressure distributions over delta wings with rhombic cross sections . a deuce programme has been written for the calculation and some of the results are compared with those of slender thin wing theory .",
      "source": "reconstructed-from-retrieval-pools-gen017"
    },
    {
      "id": "247",
      "score": 8.9783535,
      "title": "the calculation of the pressure distribution on thick wings of small aspect ratio at zero lift in subsonic flow .",
      "abstract": "the calculation of the pressure distribution on thick wings of small aspect ratio at zero lift in subsonic flow . the method of expressing the velocity increment over aerofoils directly in terms of the section ordinates wings of finite aspect ratio . the wings considered are untapered in plan-form but may be tapered in thickness . the section can be of any given shape so that in this sense the analysis is more general than that of refs. 3 to 6 which deal with wings of biconvex section . the coefficients required in the calculation are tabulated for the centre-section of straight and swept-back wings of aspect ratios 0.5,. 1,. 2,. and 4, the wing of infinite aspect ratio having been treated in ref. 1 . the remaining calculations can be made very quickly . since wings of very small aspect ratio can be treated also by the method of slender-body theory, the relations between linear theory, slender-body theory, and linearised slender-body theory are discussed . for the special case of ellipsoids, the results obtained from the various methods are compared with the exact solution .",
      "source": "reconstructed-from-retrieval-pools-gen017"
    },
    {
      "id": "545",
      "score": 8.9783535,
      "title": "calculation of sideslip derivatives and pressure distribution in asymmetric flight conditions on a slender wing-fin configuration .",
      "abstract": "calculation of sideslip derivatives and pressure distribution in asymmetric flight conditions on a slender wing-fin configuration . the flow around slender wing-fin configurations having curved leading edges, whose shape is defined by polynomials, is considered . a general expression for the pressure distribution on such a configuration in asymmetric flow is derived and the derivatives due to the particular case of sideslipping motion are also given . no numerical results are given for wing-fin load distribution, but the sideslip derivatives have been evaluated in a number of cases for gothic and ogee wings .",
      "source": "reconstructed-from-retrieval-pools-gen017"
    },
    {
      "id": "675",
      "score": 8.9783535,
      "title": "pressure distribution and surface flow on 5( and 9( thick wings with curved tip and 60degree sweepback .",
      "abstract": "pressure distribution and surface flow on 5( and 9( thick wings with curved tip and 60degree sweepback . extensive tables are given of pressure coefficients measured at reynolds numbers from 1.3x10 to 3.9x10 on two half-models of identical planform with 5( rae 101 and 9( rae 101 streamwise sections . the planform of aspect ratio 3.899 has a straight trailing edge with 60degree of sweepback, constant chord over most of the span and a parabolic outer portion of the leading edge curving to a pointed tip . the overall wing characteristics are obtained from integrated normal pressures and are compared with lifting-surface theory . the low-speed experimental pressure distributions and surface oil-flow patterns are analysed and discussed in relation to the onset of separation and the distinct vortex flows that develop at high incidence . series of contrasting upper-surface isobars illustrate some features of the different stalling processes of the two wings . the direct influence of the main vortex on local surface pressures is assessed in general terms . a fuller appraisal of secondary surface flow is obtained from the oil patterns, observations in water and measurements of high suction near the trailing edge . studies of the extent of leading-edge stall and location of part-span vortices, in particular two simultaneous leading-edge vortices on the thinner wing, follow from further analysis of local surface pressures . after a detailed discussion of the effect of reynolds number and the distinct types of separated flow, a few results with leading-edge roughness are considered in relation to scale effect on separation and the extensive influence of part-span roughness .",
      "source": "reconstructed-from-retrieval-pools-gen017"
    },
    {
      "id": "612",
      "score": 8.620918,
      "title": "pressure distributions and flow patterns at m=4 . on some delta wings of inverted 'v' cross section .",
      "abstract": "pressure distributions and flow patterns at m=4 . on some delta wings of inverted 'v' cross section . wind tunnel tests have been made to measure pressure distributions and to study flow patterns on a series of delta wings of inverted 'v' cross-section . each of these wings was designed to have a plane shock wave in the plane of the leading edges at a chosen mach number and incidence . it was found that for a wide incidence range about the design point the shock wave remained virtually attached to the leading edges and at each incidence the pressure was approximately constant over the lower surface .",
      "source": "reconstructed-from-retrieval-pools-gen017"
    },
    {
      "id": "1090",
      "score": 8.620918,
      "title": "pressure distribution and force measurements on a vtol tilting wing-propeller model . pt .ii, analysis of results .",
      "abstract": "pressure distribution and force measurements on a vtol tilting wing-propeller model . pt .ii, analysis of results . this report presents in graphical form the results presented in reference 1 from pressure distribution and force measurements on a half-wing model of a twin-engined tilt-wing vtol configuration . the profound influence of the slipstream on these results is discussed in some detail .",
      "source": "reconstructed-from-retrieval-pools-gen017"
    },
    {
      "id": "1261",
      "score": 8.432706,
      "title": "a method of calculating velocity distribution for turbulent boundary layers in adverse pressure distributions .",
      "abstract": "a method of calculating velocity distribution for turbulent boundary layers in adverse pressure distributions . a new method of calculating the behavior of turbulent boundary layers in adverse pressure distributions is developed which permits direct determination of the velocity profile rather than the gross integral parameters normally used to infer the general character of the boundary layer . the method offers the simplicity of algebraic equations coupled with the use of charts rather than the laborious simultaneous solution of coupled differential equations required by existing methods . the method also affords, for the first time, a means of determining the total boundary-layer thickness, thus allowing calculation of the absolute as well as the nondimensional velocity distribution . the velocity profile is considered to be composed of two regions--an inner region which is described by the law of the wall and an outer region which is described by a function depicting the deviation from that law . the deviation function involves two parameters which are uniquely dependent upon the skin-friction coefficient and a third parameter which, for practical purposes, can be considered a constant . since the entire velocity distribution was found to be almost uniquely dependent upon the local skin friction, serious doubt is cast upon the generally accepted /history concept/ which considers the outer region of the boundary layer to be dependent on integrated upstream conditions . agreement between experimental velocity distributions and those calculated by the method presented here is generally very good . the analysis and calculation procedures which are presented are applicable to two-dimensional, pseudo-two- dimensional, and axisymmetric conical flows .",
      "source": "reconstructed-from-retrieval-pools-gen017"
    },
    {
      "id": "38",
      "score": 8.37971,
      "title": "on the prediction of mixed subsonic/supersonic pressure distributions .",
      "abstract": "on the prediction of mixed subsonic/supersonic pressure distributions . high-speed wind-tunnel results are analyzed to derive a semiempirical scheme for the prediction of transonic pressure distributions . the supersonic and subsonic parts of the flow are treated separately, and then linked by an empirical shock pressure rise relation . the significance of the empirical results is considered in relation to the physical mechanism of transonic flows . it is also shown that theoretical solutions can be improved by introducing the empirical shock relation .",
      "source": "reconstructed-from-retrieval-pools-gen017"
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