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  • 1
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    Unknown
    Wind-tunnel tests of a Clark Y wing with a narrow auxiliary airfoil in different positions (1933)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Aerodynamic force tests were made on a combination of a Clark Y wing and a narrow auxiliary airfoil to find the best location of the auxiliary airfoil with respect to the main wing. The auxiliary was a highly cambered airfoil of medium thickness having a chord 14.5 per cent that of the main wing. It was tested in 141 different positions ahead of, above, and behind the nose portion of the main wing, the range of the test points being extended until the best aerodynamic conditions were covered. A range of positions was found in which the combination of main wing and auxiliary gave substantially greater aerodynamic efficiency and higher maximum lift coefficients (based on total area) than the main Clark Y wing alone. In the optimum position tested, considering both the maximum lift and the speed-range ratio, the combination of main wing and auxiliary gave an increase in the maximum lift coefficient of 32 per cent together with an increase in the ratio of 21 per cent of the respective values for the main Clark Y wing alone.
    Type: NACA-TR-428
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Effects of some present-day airplane design trends on requirements for lateral stability (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Type: NACA-TN-814
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Aerodynamic rolling and yawing moments produced by floating wing-tip ailerons, as measured by spinning balance (1934)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The investigation described in this report was made to determine the effectiveness of floating wing-tip ailerons as an airplane control in the spin. In these tests the ailerons, not being balanced, were set parallel to the axis of rotation, which is probably very nearly the attitude that balanced floating ailerons would assume in a spin. The tests were made with the spinning balance in the N.A.C.A. 5-foot vertical tunnel. The model was tested with and without the ailerons in 12 spinning attitudes chosen to cover the probable spinning range. Rolling- and yawing-moment coefficients are given as measured for the model with and without the ailerons, and computed values are given for the ailerons alone. The addition of floating wing-tip ailerons to the model doubled the rolling-moment coefficient and increased the yawing-moment coefficient by 0.05 and more. Both moments were in a sense to oppose the spin.
    Type: NACA-TN-493
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Wind-tunnel of three lateral-control devices in combination with a full-span slotted flap on an NACA 23012 airfoil (1938)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A large-chord NACA 23012 airfoil was tested. The airfoil extended completely across the test section, and two-dimensional flow was approximated. The model was fitted with a full-span slotted flap having a chord 25.66 percent of the airfoil chord. The ailerons investigated extended over the entire span and each had a chord 10 percent of the airfoil chord. The types of ailerons tested were: retractable ailerons, slot-lip ailerons using the lip of the slot for ailerons, and plain ailerons on the trailing edge of the slotted flap. The data are presented in the form of curves of section lift, drag, and pitching-moment coefficients for the airfoil with flap deflected but with ailerons neutral, and of rolling-moment, yawing-moment, and hinge-moment coefficients calculated for a rectangular wing of aspect ratio 6 with a semi-span aileron and a full-span flap. For the ailerons investigated the data indicate that, from considerations of rolling and yawing moments produced and of stick forces desired, the retractable aileron is the most satisfactory means of lateral control for use with a full-span slotted flap.
    Type: NACA-TN-659
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Wind Tunnel Tests on a Model of a Monoplane Wing with Floating Ailerons (1929)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report describes preliminary wind tunnel tests on a model of a monoplane wing equipped with wing tip floating ailerons. Lift and drag, as well as rolling and yawing moments, were measured.
    Type: NACA-TN-316
    Format: application/pdf
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  • 6
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    Wind Tunnel Tests on an Airfoil Equipped with a Split Flap and a Slot (1929)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The investigation described in this report is concerned with the changes in the aerodynamic characteristics of an airfoil which are produced by a gauze-covered suction slot, located near the leading edge, and connected by an air passage to a split flap at the trailing edge. The tests were conducted at the Langley Memorial Aeronautical Laboratory. At the larger values of lift coefficient where the action of the slot might be expected to be most effective, the pressure differences were such that the air flowed out of the slot rather than in through it, and in consequence, the maximum lift coefficient was decreased.
    Type: NACA-TN-324
    Format: application/pdf
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  • 7
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    Wind tunnel tests on airfoil boundary control using a backward opening slot (1929)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of an investigation to determine the effect of boundary layer control on the lift and drag of an airfoil equipped with a backward opening slot. Various slot locations, widths of opening, and pressures, were used. The tests were conducted in the Five-Foot Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory. The greatest increase in maximum lift was 96 per cent, the greatest decrease in minimum drag was 27 per cent, and the greatest increase in the ratio, maximum lift coefficient/minimum drag coefficient, was 151 per cent.
    Type: NACA-TN-323
    Format: application/pdf
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  • 8
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    Preliminary report on the flat-top lift curve as a factor in control at low speed (1928)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report is concerned with the importance of the flat-top lift curve as a factor contributing to safety and control at low speed. An analysis of existing airfoil data indicated definite relations between the shape of the lift curve and certain section dimensions.
    Type: NACA-TN-297
    Format: application/pdf
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  • 9
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    Wind-Tunnel Tests on Airfoil Boundary Layer Control Using a Backward-Opening Slot (1932)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: This report presents the results of an investigation to determine the effect of boundary layer control on the lift and drag of an airfoil. Boundary layer control was accomplished by means of a backward-opening slot in the upper surface of the hollow airfoil. Air was caused to flow through this slot by a pressure which was maintained inside the airfoil by a blower. Various slot locations, slot openings, and wing pressures were used. The tests were conducted in the 5-foot atmospheric wind tunnel of the Langley Memorial Aeronautical Laboratory. Under the test conditions, the maximum lift coefficient was increased about 96 per cent for one slot arrangement, and the minimum drag coefficient was decreased about 27 per cent for another, both being compared with the results obtained with the unslotted airfoil. It is believed from this investigation that the above effects may be increased by the use of larger slot openings, better slot locations, multiple slots, improved airfoil profiles, and trailing edge flaps.
    Type: NACA-TR-385
    Format: application/pdf
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