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  • Aircraft Design, Testing and Performance  (8)
  • 1960-1964
  • 1950-1954
  • 1935-1939  (8)
  • 1939  (8)
Collection
Keywords
Years
  • 1960-1964
  • 1950-1954
  • 1935-1939  (8)
Year
  • 1
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    Unknown
    A Flight Determination of the Moments of the YG-1B Tapered Blade Rotor about the Hub Trunnions (1939)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: At the request of the Materiel Division, Wright Field, the National Advisory Committee for Aeronautics is conducting a program of flight tests on a Kellett YG-1B autogiro equipped with a new type of rotor blade. The new blades are tapered in both plan form. and thickness and are designed to avoid periodic blade twist. One phase of the investigation, involving determination of the moments of the resultant rotor force about the trunnions on which the hub is pivoted for control, has been completed. The results obtained are reported herein.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-MR-X-1939
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Preliminary Model Tests of a Wing-Duct Cooling System for Radial Engines, Special Report (1939)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Wind-tunnel tests were conducted on a model wing-nacelle combination to determine the practicability of cooling radial engines by forcing the cooling air into wing-duct entrances located in the propeller slipstream, passing the air through the engine baffles from rear to front, and ejecting the air through an annular slot near the front of the nacelle. The tests, which were of a preliminary nature, were made on a 5-foot-chord wing and a 20-inch-diameter nacelle. A 3-blade, 4-foot-diameter propeller was used. The tests indicated that this method of cooling and cowling radial engines is entirely practicable providing the wing of the prospective airplane is sufficiently thick to accommodate efficient entrance ducts , The drag of the cowlings tested was definitely less than for the conventional N.A.C.A. cowling, and the pressure available at low air speed corresponding to operation on the ground and at low flying speeds was apparently sufficient for cooling most present-day radial engines.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-101
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    An Electrical-Type Indicating Fuel Flowmeter (1939)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: An electrical-type meter has been developed for measuring mass rates of flow of gasoline or other nonconducting fluids. Its temperature dependence is small over a large range and it has no known vibrational or viscosity errors. The maximum temperature rise is less than 5 C. The rates of flow, measurable within 1% with the present instrument, are approximately 100 to 1,000 or more pounds of gasoline per hour when a potentiometer is used, or 100 to 300 pounds per hour when a deflection-type meter is used.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-12
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    The Calculated Effect of Various Hydrodynamic and Aerodynamic Factors on the Take-Off of a Large Flying Boat (1939)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: Present designs for large flying boats are characterized by high wing loading, high aspect ratio, and low parasite drag. The high wing loading results in the universal use of flaps for reducing the takeoff and landing speeds. These factors have an effect on takeoff performance and influence to a certain extent the design of the hull. An investigation was made of the influence of various factors and design parameters on the takeoff performance of a hypothetical large flying boat by means of takeoff calculations. The parameters varied in the calculations were size of hull (load coefficient), wing setting, trim, deflection of flap, wing loading, aspect ratio, and parasite drag. The takeoff times and distances were calculated to the stalling speeds and the performance above these speeds was studied separately to determine piloting technique for optimum takeoff. The advantage of quick deflection of the flap at high water speeds is shown.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-119
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Radiator Design and Installation (1939)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The fundamental principles of fluid flow, pressure losses, and heat transfer have been presented and analyzed for the case of a smooth tube with fully developed turbulent flow. These equations apply to tubes with large length-diameter ratios where the f1ow is at a high Reynolds Number. The error introduced by using these equations increases as the magnitude of the tube length and the air-flow Reynolds Number approaches the values encountered in modern radiator designs. Accordingly, heat-transfer tests on radiator sections were made and the results are presented in nondimensional form to facilitate their use and for comparison with other heat-transfer data. In addition, pressure losses were measured along smooth tubes of circular, square, and rectangular cross section and the results were also correlated and are presented in nondimensional form. The problem of a radiator design for a particular installation is solved, the experimental heat-transfer and pressure-loss data being used, on a basis of power chargeable to the radiator for form drag, for propelling the weight, and for forcing the air through the radiator. The case of an installation within a wing or an engine nacelle is considered. An illustration of radiator design is carried through for an arbitrary set of conditions. Sufficient detail is given to enable the reader to reproduce the analysis for any given case.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-112
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    An Investigation of the Drag of Windshields in the 8-Foot High-Speed Wind Tunnel (1939)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: The drag of closed-cockpit and transport-type windshields was determined from tests made at speeds from 200 to 440 miles per hour in the NACA 8-foot high-speed wind tunnel. This speed range corresponds to a test Reynolds number range of 2,510,000 to 4,830,000 based on the mean aerodynamic chord of the full-span model (17.29 inches). The shapes of the windshield proper, the hood, and the tail fairing were systematically varied to include common types and a refined design. Transport types varied from a reproduction of a current type to a completely faired windshield. The results show that the drag of windshields of the same frontal area, on airplanes of small to medium size, may account for 15% of the airplane drag or may be reduced to 1%. Optimum values are given for windshield and tail-fairing lengths; the effect, at various radii is shown. The longitudinal profile of a windshield is shown to be most important and the transverse profile, to be much less important. The effects of retaining strips, of steps for telescoping hoods, and of recessed windows are determined. The results show that the drag of transport-type windshields may account for 21% of the fuselage drag or may be reduced to 2%.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-114
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Intercooler Design for Aircraft, Special Report (1939)
    In:  CASI
    Details
    Publication Date: 2019-07-12
    Description: When an airplane is operating at high altitude, it is necessary to use a supercharger to maintain ground pressure at the carburetor inlet. This maintenance and high intake-manifold pressure tends to keep the power output of the engine at ground-level value. The air, being compressed by the supercharger, however, is heated by adiabatic compression and friction to a temperature that seriously affect the performance of the engine. It is thus necessary to use an intercooler to reduce the temperature of the air between the supercharger outlet and the carburetor inlet. The amount of cooling required of the intercooler depend on the efficiency of the supercharger installation. In this investigation, several types of intercoolers were compared and a design procedure that will give the best intercooler for a given set of conditions is indicated. The figure of merit used for the selection of the best design was the total power consumed by the intercooler. This value includes the power required to transport the weight of the intercooler as well as the power used to force the charge air and the cooling air through the intercooler. The cost, size and practicality of construction were not considered, inasmuch as it was thought that a survey of possibilities of improvement in design would be of interest, regardless of whether the improvement could be immediately realized. Three types of intercoolers are included in this survey: a counterflow intercooler with indirect cooling surface in the form of fins, a counterflow intercooler with direct cooling surfaces, and a cross-flow, tube-type intercooler.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-124
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Pressure Distribution on the Fuselage of a Midwing Airplane Model at High Speeds (1939)
    In:  CASI
    Details
    Publication Date: 2019-08-26
    Description: The pressure distribution on the fuselage of a midwing airplane model was measured in the NACA 8-foot high speed wind tunnel at speeds from 140 to 440 miles per hour for lift coefficients ranging from -0.2 to 1.0. The primary purpose of the tests was to provide data showing the air pressures on various parts of the fuselage for use in structural design. The data may also be used for the design of scoops and vents. The results show that the highest negative pressures occurred near the wing and were more dependent on the wing than on the fuselage. At high speeds, the magnitude of the pressure coefficients as predicted from pressure coefficients determined experimentally at low speeds by application of the theoretical factor 1/(square root)1-M(exp 2) (where M is the ratio of the air speed to the speed of sound in air) may misrepresent the actual conditions. At the points where the maximum negative pressures ocurred, however, the variation of the pressure coefficients was in good agreement with the theoretical factor, indicating that this factor may afford satisfactory predictions of critical speed, at least for fuselages similar to the shape tested.
    Keywords: Aircraft Design, Testing and Performance
    Type: NACA-SR-133
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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