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  • 1
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    Unknown
    Reduction of lift of a wing due to its drag (1935)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This analysis computes for a predetermined airfoil and given Reynolds Number the course of the "displacement thickness," i.e., the course of the layer by which the streamlines of the potential flow are pushed away from the wing through the frictional layer. The result is, to a certain extent, a new wing contour.
    Type: NACA-TM-781
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    An Airfoil Spanning an Open Jet (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Proceeding from the fundamental problem on the mutual relation of a wing and free boundaries the distribution of the circulation is determined for an airfoil spanning an open jet of rectangular section at different aspect ratios, and then for an open jet of circular section. The solution is obtained by means of a Fourier series and computations have been performed for different values of the variables. The second part describes the experiments performed for the purpose of proving the theory. The results confirm the theory. In conclusion it defines the induced drag of a wing extending across an open jet and compares it with the drag of a monoplane having a span equal to the jet width at equal total lift.
    Type: NACA-TM-723
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Contribution to the Problem of Airfoils Spanning a Free Jet (1936)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: After a brief discussion of the work done up to now on an unwarped wing of constant chord spanning a free jet, the computation of the circulation and lift distribution for different forms of warped wings spanning rectangular and circular jets was carried out. The computed values are compared with test values and the agreement is found to be good. The effect of placing the wing eccentrically is slight and may be applied as a correction factor to the data obtained for wing placed in middle of jet.
    Type: NACA-TM-796
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Unknown
    Effect of Propeller Slipstream on Wing and Tail (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The results of wind tunnel tests for the determination of the effect of a jet on the lift and downwash of a wing are presented in this report. In the first part, a jet without rotation and with constant velocity distribution is considered - the jet being produced by a specially designed fan. Three-component, pressure distribution, and downwash measurements were made and the results compared with existing theory. The effect of a propeller slipstream was investigated in the second part. In the two cases the jet axis coincided with the undisturbed wind direction. In the third part the effect of the inclination of the propeller axis to the wing chord was considered, the results being obtained for a model wing with running propeller.
    Type: NACA-TM-874
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Unknown
    Investigation of Boundary Layers on an Airplane Wing in Free Flight (1934)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes the equipment and method developed for recording the boundary layers on the surface of an airfoil in free flight. The results are in close agreement with the wind-tunnel tests of other experimenters. The intensity of the turbulent boundary layer, even at the much higher Reynolds Numbers reached, is determinable with Gruschwitz's formulas, although it was impossible to definitely establish a direct relationship between the turbulent boundary layer and the Reynolds Number within the limits of the obtained accuracy. The observations on the transition from laminar to turbulent flow check with previous wind-tunnel tests and calculations.
    Type: NACA-TM-751
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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