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  • 1
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    Preliminary Results of Flight Tests of a Conventional Three-Blade Propeller at High Speeds (1942)
    In:  CASI
    Details
    Publication Date: 2018-06-05
    Description: As part of the program of flight tests of airplane propellers to determine compressibility effects at high speeds, preliminary flights have been made with a conventional three-blade propeller (Hamilton Standard 3155-6) on a Bell YP-39 airplane. This preliminary report presents the high-speed data obtained thus far with a brief analysis of the results.
    Keywords: Aerodynamics
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Notes on the Stability and Control of Tailless Airplanes (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Problems involved in the stability and control of tailless airplanes are discussed. Such factors as the location of the aerodynamic center and its effect on the longitudinal stability, longitudinal trim with high-lift devices, the effects of various changes in the shape of the wing on lateral stability, and the effects of nacelles are covered. It appears that sufficient stability and controllability can be secured without sweepback. With sweepback, a flap over the center section of the wing may be used to serve the dual purpose of elevator control and high-lift device. Sweepback introduces undesirable stalling characteristics, however, and may require auxiliary devices to prevent stalling of the tips.
    Keywords: Aerodynamics
    Type: NACA-TN-837
    Format: application/pdf
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  • 3
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    Investigation of the Behavior of Parallel Two-Dimensional Air Jets (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An investigation was made of the flow downstream from a "two-dimensional" grid formed of parallel rods. In both two and three dimensional jet fields there is a critical range of grid density below which the downstream flow is stable and above which it is unstable. The flow can be completely stabilized by means of an adequate lateral contraction beginning immediately after the grid or by use of a fine-mesh damping screen parallel to the grid plane and within a definite range of positions downstream from the grid.
    Keywords: Aerodynamics
    Type: NACA-WR-W-90 , NACA-ACR-4H24
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    The Selection of Propellers for High Thrust at Low Airspeed (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Problem of improving thrust at low speeds is primarily one of reducing angle of attack of operation of sections to improve L/D or reducing blade helix angle. An analysis, based on recent propeller data, is presented for determining improvements in thrust or efficiency which could be obtained by increased number of blades, increased blade width, increased diameter, dual rotation, and two-speed gearing. All methods were found very effective, particularly two-speed gearing.
    Keywords: Aerodynamics
    Type: NACA-WR-L-483
    Format: application/pdf
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  • 5
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    High-speed Tests of a Ducted Body with Various Air-outlet Openings (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Test of a ducted body with Internal flow were made in the 8-foot high-speed wind tunnel for the purpose of studying the effects on external drag and an critical speed of the addition of efficient inlet and outlet openings to a basic streamline shape. Drag tests of a 13.6- inch-diameter streamline body of fineness ratio 6.14 were made at Mach numbers ranging from 0.20 to 0.75. The model was centrally mounted on a 9-percent-thick airfoil and was designed to have an efficient airfoil-body juncture and a high critical speed. An air inlet at the nose and various outlets at the tail were added: drag and internal-flow data were obtained over the given speed range. The critical speed of the ducted bodies was found to be as high as that of the streamline body. The external - drag with air flow through the body did not exceed the drag of the basic streamline shape. No appreciable variation in the efficiency of the diffuser section of the internal duct occurred throughout the Mach number range of the tests.
    Keywords: Aerodynamics
    Type: NACA-WR-L-486
    Format: application/pdf
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  • 6
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    The Longitudinal Stability of Flying Boats as Determined by Tests of Models in the NACA Tank II : Effect of Variations in Form of Hull on Longitudinal Stability (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Data taken from tests at constant speed to establish trim limits of stability, tests at accelerated speeds to determine stable limits of center of gravity shift, and tests at decelerated speeds to obtain landing characteristics of several model hull forms were used to establish hull design effect on longitudinal stability of porpoising. Results show a reduction of dead rise angle as being the only investigated factor reducing low trim limit. Various methods of reducing afterbody interference increased upper trim limit
    Keywords: Aerodynamics
    Type: NACA-WR-L-468
    Format: application/pdf
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  • 7
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    Effect of Normal Pressure on the Critical Shear Stress of Curved Sheet (1943)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: In order to determine the critical stresses caused by an outward acting pressure on the upper surface of a wing due to the difference in internal and external pressures, torsional tests were made on two curved-sheet specimens subjected to an outward acting normal pressure. Results show that an outward acting normal pressure appreciable raises the critical shear stress for an unstiffened curved sheet; the absolute increase in critical shear stress is slightly greater for a 30 in. rib spacing than for a 10 in. rib spacing.
    Keywords: Aerodynamics
    Type: NACA-WR-L-416
    Format: application/pdf
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  • 8
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    The Characteristics of Two Model Six-blade Counterrotating Pusher Propellers of Conventional and Improved Aerodynamic Design (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Two airfoil plans were used for propeller blades. One is modified Clark Y section designed for structural reliability and the second an NACA 16 airfoil section designed to produce minimum aerodynamic losses. At low air speeds, the propeller designed for aerodynamic effects showed a gain of from 1.5 to 4.0 percent in propulsive efficiency over the conventional type depending on the pitch. Because of the numerous variables involved, the effect of each one on the aerodynamic characteristics of the propellers could not be isolated.
    Keywords: Aerodynamics
    Type: NACA-WR-L-404
    Format: application/pdf
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  • 9
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    Flight Investigation of Wing-gun Fairings on a Fighter Type Airplane (1941)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Description is given of flight tests conducted on gun fairings, designed to correct the detrimental effects of the projecting and submerged wing guns on an F4F-3 fighter. It was found that the installation of unfaired guns on a clean wing resulted in a premature stall that increased the stalling speed in the carrier-approach and landing conditions of flight by suitably fairing the guns, it was possible to reduce the stalling speeds to values approaching very nearly the clean-wing values.
    Keywords: Aerodynamics
    Type: NACA-WR-L-247
    Format: application/pdf
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  • 10
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    The Porpoising Characteristics of a Planing Surface Representing the Forebody of a Flying-Boat Hull (1942)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Porpoising characteristics were observed on V-body fitted with tail surfaces for different combinations of load, speed, moment of inertia, location of pivot, elevator setting, and tail area. A critical trim was found which was unaltered by elevator setting or tail area. Critical trim was lowered by moving pivot either forward or down or increasing radius or gyration. Increase in mass and moment of inertia increased amplitude of oscillations. Complete results are tabulated and shown graphically.
    Keywords: Aerodynamics
    Type: NACA-WR-L-479
    Format: application/pdf
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