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The Drag of Streamline Wires

Description: "Preliminary results are given of drag tests of streamline wires. Full-size wires were tested over a wide range of speeds in the N.A.C.A. high speed tunnel. The results are thus directly applicable to full-scale problems and include any compressibility effects encountered at the higher speeds. The results show how protuberances may be employed on conventional streamline wires to reduce the drag, and also show how the conventional wires compare with others having sections more like strut or symmetrical airfoil sections" (p. 1).
Date: December 1933
Creator: Jacobs, Eastman N.
Partner: UNT Libraries Government Documents Department

Effect of Viscosity on Fuel Leakage Between Lapped Plungers and Sleeves and on the Discharge From a Pump-Injection System

Description: "Test data and analysis show that the rate of fuel leakage between a lapped plunger and sleeve varies directly with the density of the fuel, the diameter of the plunger, the pressure producing the leakage, and the cube of the mean clearance between the plunger and sleeve. The rate varies inversely as the length of the lapped fit and the viscosity of the fuel. With a mean clearance between the plunger and sleeve of 0.0001 inch the leakage amounts to approximately 0.2 percent of the fuel injected with gasoline and as low as 0.01 percent with diesel fuel oils" (p. 63).
Date: December 13, 1933
Creator: Rothrock, A. M. & Marsh, E. T.
Partner: UNT Libraries Government Documents Department

Practical Experiences With Lightning Discharges to Airplanes

Description: The present report describes many cases of airplanes being struck by lightning and the measures that can be taken to minimize damage to them. The data indicates that the hazard to airplanes from lightning is overestimated and that dangers can be minimized by appropriate weather forecasts and training of the pilots.
Date: December 1933
Creator: Koppe, Heinrich
Partner: UNT Libraries Government Documents Department

Trend of Airplane Flight Characteristics

Description: This report describes the development of airplane characteristics since the war and indicates the direction development should take in the immediate future. Some of the major topics include: the behavior of an airplane about its lateral, vertical, and longitudinal axes. Behavior at large angles of attack and landing characteristics are also included.
Date: December 1933
Creator: Von Köppen, Joachim
Partner: UNT Libraries Government Documents Department

Strength Tests of Thin-Walled Duralumin Cylinders in Pure Bending

Description: "This report is the third of a series presenting the results of strengths tests on thin-walled cylinders and truncated cones of circular and elliptic section; it includes the results obtained from pure bending tests on 58 thin-walled duralumin cylinders of circular section with ends clamped to rigid bulkheads. The tests show that the stress on the extreme fiber at failure as calculated by the ordinary theory of bending is from 30 to 80 percent greater than the compressive stress at failure for thin-walled cylinders in compression. The tests also show that length/radius ratio has no consistent effect upon the bending strength and that the size of the wrinkles that form on the compression half of a cylinder in bending is approximately equal to the size of the wrinkles that form in the complete circumference of a cylinder of the same dimensions in compression" (p. 1).
Date: December 1933
Creator: Lundquist, Eugene E.
Partner: UNT Libraries Government Documents Department

The Flight of an Autogiro at High Speed

Description: This report presents a method for computing the flight performance of an autogiro at high speed, the velocity component along the blades being accounted for by calculation of the profile drag and the equation for zero torque.
Date: December 1933
Creator: Bennett, J. A.
Partner: UNT Libraries Government Documents Department

Wing-Fuselage Interference, Tail Buffeting, and Air Flow About the Tail of a Low-Wing Monoplane

Description: "This report presents the results of wind tunnel tests on a Mcdonnell Douglas airplane to determine the wing-fuselage interference of a low-wing monoplane. The tests included a study of tail buffeting and the air flow in the region of the tail. The airplane was tested with and without the propeller slipstream, both in the original condition and with several devices designed to reduce or eliminate tail buffeting. The devices used were wing-fuselage fillets, a NACA cowling, reflexed trailing edge of the wing, and stub auxiliary airfoils" (p. 143).
Date: December 13, 1933
Creator: White, James A. & Hood, Manley J.
Partner: UNT Libraries Government Documents Department

The Dewoitine D.332 Commercial Airplane (French): A Three-Engine All-Metal Low-Wing Monoplane

Description: Circular describing the Dewoitine D.332, which is a commercial three-engine all-metal low-wing monoplane form France. Details of the construction history, wing, fuselage, power plant, landing gear, characteristics, performance, drawings, and photographs are provided.
Date: December 1933
Creator: Victor, Maurice
Partner: UNT Libraries Government Documents Department

The Reduction in Drag of a Forward-Sloping Windshield

Description: "This paper gives results of a short investigation of the drag of a forward-sloping closed-cabin windshield. The drag of the windshield in both the original and a final modified form was determined from tests in the variable-density wind tunnel. The final form of the windshield was arrived at by modifying the original as the result of flow observations in the N.A.C.A. smoke tunnel. The investigation studied the utility of the N.A.C.A. smoke tunnel as applied to reducing the drag of objects for which the full dynamic scale could not be approached in the smoke tunnel, but designers should find the results of the flow observations and drag measurements of value" (p. 1).
Date: December 1933
Creator: Jacobs, Eastman N.
Partner: UNT Libraries Government Documents Department

Flight Tests on the Lateral Control of an Airplane having a Split Flap which Retracts Ahead of Conventional Ailerons, Special Report

Description: "Since the recent more or less extensive adoption of high-lift flaps on airplane wings, the problem of providing satisfactory lateral control without sacrificing a part of the span of the flaps has become one of some importance. The difficulties have been largely a matter of obtaining satisfactory rolling moments with a smoothly graduated action, together with sufficiently small control forces throughout the entire speed range. As part of an investigation including several different lateral-control arrangements to be used with split flaps, the tests reported in this paper were made on one arrangement in which conventional ailerons of narrow chord are used, and a split flap is retracted into the under surface of the wing forward of the ailerons" (p. 1).
Date: December 1933
Creator: Weick, Fred E.
Partner: UNT Libraries Government Documents Department

Charts for determining the pitching moment of tapered wings with sweepback and twist

Description: From Summary: "This report presents a convenient method for calculating the pitching-moment characteristics of tapered wings with sweepback and twist. The method is based on the fact that the pitching-moment characteristics of a wing may be specified by giving the value of the pitching moment at zero lift and the location of the axis about which the axis is constant. Data for calculating these characteristics are presented by curves which apply to wings having a linear distribution of twist along the span and which cover a large range of aspect ratios. The curves are given for wings having straight taper and distorted elliptical plan forms. The characteristics of wings of other shapes may be determined by interpolation."
Date: December 1933
Creator: Anderson, Raymond F.
Partner: UNT Libraries Government Documents Department

The effect of spray strips on a model of the P3M-1 flying boat hull

Description: This note presents the results of a series of tests made in the N.A.C.A. tank on a one-sixth full-size model of the hull and side floats of the Navy P3M-1 flying boat for the purpose of finding a method of reducing the amount of spray thrown into the propellers of this craft when taking off and landing. The model was tested without spray strips and with five different spray-strip arrangements. The best arrangement was an improvement over the bare hull with no spray strips, but the improvement was not sufficient to be satisfactory with the propellers in the designed position.
Date: December 1933
Creator: Dawson, John R.
Partner: UNT Libraries Government Documents Department