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  • Chemistry  (1,381)
  • Aerodynamics  (39)
  • AIRCRAFT
  • Chemical Engineering
  • ddc:330
  • 1955-1959
  • 1940-1944  (1,420)
  • 1944  (562)
  • 1942  (858)
Collection
Keywords
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Years
  • 1955-1959
  • 1940-1944  (1,420)
Year
  • 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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    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
  • 3
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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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    NASA TECHNICAL REPORTS
  • 4
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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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    NASA TECHNICAL REPORTS
  • 5
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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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    NASA TECHNICAL REPORTS
  • 6
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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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    NASA TECHNICAL REPORTS
  • 7
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    Effect of Compressibility on Pressure Distribution over an Airfoil with a Slotted Frise Aileron (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Pressure distribution measurements were made over an airfoil with slotted Frise aileron up to 0.76 Mach at various angles of attack and aileron defections. Section characteristics were determined from these pressure data. Results indicated loss of aileron rolling power for deflections ranging from -12 Degrees to -19 Degrees. High stick forces for non-differential deflections incurred at high speed, which were due to overbalancing tendency of up-moving aileron, may precipitate serious control difficulties. Detailed results are presented graphically.
    Keywords: Aerodynamics
    Type: NACA-WR-L-266 , NACA-ACR-L4G12
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    A Solution of the Direct and Inverse Potential Problems for Arbitrary Cascades of Airfoils (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Methods are given of determining the potential flow plast an arbitrary cascade of airfoils and the inverse problem of determining an airfoil having a prescribed velocity distribution in cascade. Results indicated that Cartesian mapping function method may be satisfactorily extended to include cascades. Numerical calculation for computing cascades by Cartesian mapping function method is considerably greater than for single airfoils but much less than hitherto required for cascades. Detailed results are presented graphically.
    Keywords: Aerodynamics
    Type: NACA-WR-L-81 , NACA-ARR-L4K22B
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Measurements in Flight of the Lateral-Control Characteristics of an Airplane Equipped with Full-Span Zap Flaps and Simple Circular-Arc-Type Ailerons (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Flight tests were conducted on the OS2U-2 seaplane with simple circular-arc-type ailerons directly connected to the actuating torque tube. Two aileron test installations were made, differing only in the inclination of the projecting surface with the wing's upper surface. The lateral-control characteristics of the airplane were determined from data obtained in stalls and rudder-fixed aileron rolls. The revised ailerons were deficient in maximum rolling effectiveness, but were capable of controlling the rolling tendencies of the airplane near the stall.
    Keywords: Aerodynamics
    Type: NACA-WR-A-32
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    Resistance Tests of a 1/16 Size Model of the Hughes-kaiser Flying Boat, NACA Model 183 (1944)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Tank tests were made of a hull model of the Hughes-Kaiser cargo airplane for estimates of take-off performance and maximum gross load for take-off. At hump speeds, with the model free to trim, the trim and resistance were high, which resulted in a load-resistance ratio of approximately 4.0 for a gross load coefficient of 0.75. With a 4000,000-lb load, the full size craft may take off in 69 sec over a distance of 5600 ft.
    Keywords: Aerodynamics
    Type: NACA-WR-L-683
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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