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  • 1
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    Effect of protruding gasoline tanks upon the characteristics of an airfoil (1926)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-249
    Format: application/pdf
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  • 2
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    Preliminary Report on Laminar-Flow Airfoils and New Methods Adopted for Airfoil and Boundary-Layer Investigations (1939)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Recent developments in airfoil-testing methods and fundamental air-flow investigations, as applied to airfoils, are discussed. Preliminary test results, obtained under conditions relatively free from stream turbulence and other disturbances, are presented. Suitable airfoils and airfoil-design principles were developed to take advantage of the unusually extensive laminar boundary layers that may be maintained under the improved testing conditions. The results are of interest mainly in range of below 6,000,000.
    Keywords: Aerodynamics
    Type: NACA-WR-L-345
    Format: application/pdf
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  • 3
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    Interference of Wing and Fuselage from Tests of 209 Combinations in the NACA Variable-Density Tunnel (1936)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of tests of 209 simple wing-fuselage combinations made in the NACA variable-density wind tunnel to provide information regarding the effects of aerodynamic interference between wings and fuselages at a large value of Reynolds number.
    Type: NACA-TR-540
    Format: application/pdf
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  • 4
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    Airfoil Section Characteristics as Affected by Variations of the Reynolds Number (1937)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of an investigation of a systematically chosen representative group of related airfoils conducted in the NACA variable-density wind tunnel over a wide range of Reynolds number extending well into the flight range. The tests were made to provide information from which the variations of airfoil section characteristics with changes in the Reynolds number could be inferred and methods of allowing for these variations in practice could be determined. This work is one phase of an extensive and general airfoil investigation being conducted in the variable-density tunnel and extends the previously published researches concerning airfoil characteristics as affected by variations in airfoil profile determined at a single value of the Reynolds number.
    Type: NACA-TR-586
    Format: application/pdf
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  • 5
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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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  • 6
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    The aerodynamic characteristics of eight very thick airfoils from tests in the variable density wind tunnel (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Report presents the results of wind tunnel tests on a group of eight very thick airfoils having sections of the same thickness as those used near the roots of tapered airfoils. The tests were made to study certain discontinuities in the characteristic curves that have been obtained from previous tests of these airfoils, and to compare the characteristics of the different sections at values of the Reynolds number comparable with those attained in flight. The discontinuities were found to disappear as the Reynolds number was increased. The results obtained from the large-scale airfoil, a symmetrical airfoil having a thickness ratio of 21 per cent, has the best general characteristics.
    Type: NACA-TR-391
    Format: application/pdf
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  • 7
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    Characteristics of propeller sections tested in the variable density wind tunnel (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tests were carried out in the variable density wind tunnel of the National Advisory Committee for Aeronautics on six airfoil sections used by the Bureau of Aeronautics as propeller sections. The sections were tested at pressures of 1 and 20 atmospheres corresponding to Reynolds numbers of about 170,000 and 3,500,000. The results obtained, besides providing data for the design of propellers, should be of special interest because of the opportunity afforded for the study of scale effect on a family of airfoil sections having different thickness ratios. (author)
    Type: NACA-TR-259
    Format: application/pdf
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  • 8
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    The Reduction in Drag of a Forward-sloping Windshield (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This paper gives results of a short investigation of the drag of a forward-sloping closed-cabin windshield. The drag of the windshield in both the original and a final modified form was determined from tests in the variable-density wind tunnel. The final form of the windshield was arrived at by modifying the original as the result of flow observations in the N.A.C.A. smoke tunnel. The investigation studied the utility of the N.A.C.A. smoke tunnel as applied to reducing the drag of objects for which the full dynamic scale could not be approached in the smoke tunnel, but designers should find the results of the flow observations and drag measurements of value. They show that most of the large drag added by the original windshield is eliminated by the modification of the windshield to the final form.
    Type: NACA-TN-481
    Format: application/pdf
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  • 9
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    The Drag of Streamline Wires (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Preliminary results are given of drag tests of streamline wires. Full-size wires were tested over a wide range of speeds in the N.A.C.A. high speed tunnel. The results are thus directly applicable to full-scale problems and include any compressibility effects encountered at the higher speeds. The results show how protuberances may be employed on conventional streamline wires to reduce the drag, and also show how the conventional wires compare with others having sections more like strut or symmetrical airfoil sections. Because the new wire sections developed are markedly superior aerodynamically to conventional wires, it is recommended that some of them be tested in service in order to investigate their relative susceptibility to vibration and to fatigue failure.
    Type: NACA-TN-480
    Format: application/pdf
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  • 10
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    Tests of N.A.C.A. airfoils in the variable-density wind tunnel Series 230. (1936)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of tests of six airfoils having the N.A.C.A. 230 mean line and varying in thickness from 0.06c to 0.21c are presented. These results agree with previous findings in showing that aerodynamically the best section is one of moderate thickness. The data are of value mainly in connection with the design of tapered wings having sections based on the N.A.C.A. 230 mean line.
    Type: NACA-TN-567
    Format: application/pdf
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