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  • Other Sources  (9)
  • 1985-1989
  • 1930-1934  (9)
  • 1931  (9)
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  • 1985-1989
  • 1930-1934  (9)
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  • 1
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    Airfoil Pressure Distribution Investigation in the Variable Density Wind Tunnel (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of wind tunnel tests of pressure distribution measurements over one section each of six airfoils. Pressure distribution diagrams, as well as the integrated characteristics of the airfoils, are given for both a high and a low dynamic scale or, Reynolds number VL/V, for comparison with flight and other wind-tunnel tests, respectively. It is concluded that the scale effect is very important only at angles of attack near the burble. The distribution of pressure over an airfoil having a Joukowski section is compared with the theoretically derived distribution. A further study of the distribution of pressure over all of the airfoils resulted in the development of an approximate method of predicting the pressure distribution along the chord of any normal airfoil for all attitudes within the working range if the distribution at one attitude is known.
    Type: NACA-TR-353
    Format: application/pdf
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  • 2
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    Tests of six symmetrical airfoils in the variable density wind tunnel (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper is the first of a series covering an investigation of a family of airfoils all formed from a basic profile. It gives in preliminary form the results of six symmetrical airfoils, differing only in maximum thickness. The maximum thickness-to-chord ratios are 0.06, 0.09, 0.12, 0.15, 0.18, and 0.21.
    Type: NACA-TN-385
    Format: application/pdf
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  • 3
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    The variation in pressure in the cabin of an airplane in flight (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The pressure in the cabin of a Fairchild cabin monoplane wa surveyed in flight, and was found to decrease with increased air speed over the fuselage and to vary with the number and location of openings in the cabin. The maximum depression of 2.2 inches of water (equivalent pressure altitude at sea level of 152 feet) occurred at the high speed of the airplane in level flight with the cabin closed.
    Type: NACA-TN-368
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  • 4
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    Tests of N.A.C.A. airfoils in the variable density wind tunnel Series 44 and 64 (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note is one of a series covering an investigation of a number of related airfoils. It presents the results obtained from tests in the N.A.C.A. Variable Density Wind Tunnel of two groups of six airfoils each. One group, the 44 series, has a maximum mean camber of 4 percent of the chord at a position 0.4 of the chord behind the leading edge and the other group, the 64 series, has a maximum mean camber of 6 percent of the chord at the same position. The members within each group differ only in maximum thickness, the maximum thickness/chord ratios being: 0.06, 0.09, 0.12, 0.15, 0.18, and 0.21. The results are analyzed with a view to indicating the variation of the aerodynamic characteristics with profile thickness for airfoils having a certain mean camber line form.
    Type: NACA-TN-401
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  • 5
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    Tests of N.A.C.A. airfoils in the variable-density wind tunnel Series 45 and 65 (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note is one of a series covering an investigation of a number of related airfoils. It presents the results obtained from tests in N.A.C.A. Variable-Density Wind Tunnel of two groups of six airfoils each. One group, the 45 series, has a maximum mean camber of 4 per cent of the chord at a position 0.5 of the chord behind the leading edge, and the other group, the 65 series, has a maximum mean camber of 6 per cent of the chord at the same position. The members within each group differ only in maximum thickness, the maximum thickness/chord ratios being: 0.06, 0.09, 0.12, 0.15, 0.18, and 0.21. The results are analyzed with a view to indicating the variation of the aerodynamic characteristics with profile thickness for airfoils having a certain mean camber line form.
    Type: NACA-TN-392
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  • 6
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    Tests of N.A.C.A. airfoils in the variable-density wind tunnel Series 43 and 63 (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This note is one of a series covering an investigation of a family of related airfoils. It gives in preliminary form the results obtained from tests in the N.A.C.A. Variable-Density Wind Tunnel of two groups of six airfoils each. One group, the 43 series, has a maximum mean camber of 4 per cent of the chord at a position 0.3 of the chord from the leading edge; the other group, the 63 series, has a maximum mean camber of 6 per cent of the chord at the same position. The members within each group differ only in maximum thickness, the maximum thickness/chord ratios being:0.06, 0.09, 0.12, 0.15, 0.18, and 0.21. The results are analyzed with a view to indicating the variation of the aerodynamic characteristics with profile thickness for airfoils having a certain mean camber line.
    Type: NACA-TN-391
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  • 7
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    Large-scale aerodynamic characteristics of airfoils as tested in the variable density wind tunnel (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In order to give the large-scale characteristics of a variety of airfoils in a form which will be of maximum value, both for airplane design and for the study of airfoil characteristics, a collection has been made of the results of airfoil tests made at full-scale values of the reynolds number in the variable density wind tunnel of the National Advisory Committee for Aeronautics. They have been corrected for tunnel wall interference and are presented not only in the conventional form but also in a form which facilitates the comparison of airfoils and from which corrections may be easily made to any aspect ratio. An example showing the method of correcting the results to a desired aspect ratio has been given for the convenience of designers. In addition, the data have been analyzed with a view to finding the variation of the aerodynamic characteristics of airfoils with their thickness and camber.
    Type: NACA-TR-352
    Format: application/pdf
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  • 8
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    On Atomization in Carburetors (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The outstanding quantity of the whole atomization problem is the characteristic K, and therefore the ratio of the static pressure of the air stream with respect to the liquid to the surface tension of the liquid. The higher its value, the better the atomization. The shape of the Venturi tube plays a secondary role. The increase of section beyond the throat had best not be too abrupt.
    Type: NACA-TM-644
    Format: application/pdf
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  • 9
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    Pressure Distribution Over a Symmetrical Airfoil Section with Trailing Edge Flap (1931)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Measurements were made to determine the distribution of pressure over one section of an R. A. F. 30 (symmetrical) airfoil with trailing edge flaps. In order to study the effect of scale measurements were made with air densities of approximately 1 and 20 atmospheres. Isometric diagrams of pressure distribution are given to show the effect of change in incidence, flap displacement, and scale upon the distribution. Plots of normal force coefficient versus angle of attack for different flap displacements are given to show the effect of a displaced flap. Plots are given of both the experimental and theoretical characteristic coefficients versus flap angle, in order to provide a comparison with the theory. It is concluded that for small flap displacements the agreement for the pitching and hinge moments is such that it warrants the use of the theoretical parameters. However, the agreement for the lift is not as good, particularly for the smaller flaps. In an appendix, an example is given of the calculation of the load and moments on an airfoil with hinged flap from these parameters.
    Type: NACA-TR-360
    Format: application/pdf
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