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The Drag and Interference of a Nacelle in the Presence of a Wing

Description: A wing interference investigation was conducted to determine why the N.A.C.A. cowling did not yield the expected increase in speed when adapted to the outboard nacelles of trimotored airplanes. The results indicate that the drag and interference of the engine nacelle with the cowling, when combined with a thick wing, can be reduced from its value as originally applied by changing its position and fairing it into the wing.
Date: October 1929
Creator: Jacobs, Eastman N.
Partner: UNT Libraries Government Documents Department
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The Impact on Seaplane Floats During Landing

Description: "In order to make a stress analysis of seaplane floats, and especially of the members connecting the floats with the fuselage, it is of great importance to determine the maximum pressure acting on the floats during landing. Here, the author gives a formula for maximum pressures during landing that permits one to apply experimental results to different bodies and different velocities. The author notes that the formula checks very well with experimental results" (p. 1).
Date: October 1929
Creator: von Karman, T.
Partner: UNT Libraries Government Documents Department
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The effect of the wings of single engine airplanes on propulsive efficiency as shown by full scale wind tunnel tests

Description: An investigation was conducted to determine the effect of the wings on propulsive efficiency. The wings are shown to cause a reduction of 1 percent to 3 percent in propulsive efficiency, which is about the same for monoplane as well as biplane wings.
Date: October 1929
Creator: Weick, Fred E. & Wood, Donald H.
Partner: UNT Libraries Government Documents Department
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Wind tunnel pressure distribution tests on a series of biplane wing models Part II: effects of changes in decalage, dihedral, sweepback and overhang

Description: This preliminary report furnishes information on the changes in the forces on each wing of a biplane cellule when the decalage, dihedral, sweepback and overhang are separately varied. The data were obtained from pressure distribution tests made in the Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory. Since each test was carried up to 90 degree angle of attack, the results may be used in the study of stalled flight and of spinning and in the structural design of biplane wi… more
Date: October 1929
Creator: Knight, Montgomery & Noyes, Richard W.
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Pressure Distribution Tests on an Airfoil With Trailing Edge Flap

Description: "This report deals with pressure distribution tests on an airfoil with a conventional trailing edge flap. These tests were conducted in the Atmospheric Wind Tunnel of the National Advisory Committee for Aeronautics. Maximum chord loadings were obtained with the flap displaced downward and with the airfoil at large angles of attack. Greater changes were produced in the normal force and in the center of pressure travel by up-flap than by an equal down-flap displacement" (p. 1).
Date: October 1929
Creator: Wenzinger, Carl J. & Loeser, Oscar, Jr.
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Tests on Airfoil Boundary Control Using a Backward Opening Slot (1929)

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" (p. 1).
Date: October 1929
Creator: Knight, Montgomery & Bamber, Millard J.
Partner: UNT Libraries Government Documents Department
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Wind Tunnel Tests on an Airfoil Equipped With a Split Flap and a Slot

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… more
Date: October 1929
Creator: Bamber, Millard J.
Partner: UNT Libraries Government Documents Department
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Bearing Strength of Wood Under Steel Aircraft Bolts and Washers and Other Factors Influencing Fitting Design

Description: The purpose of this report is to correlate, bring up to date, and put under a single cover all the information thought to be essential to an understanding of the formulas regarding bearing strength of wood under steel aircraft bolts and washers and other factors influencing fitting design.
Date: October 1928
Creator: Trayer, G. W.
Partner: UNT Libraries Government Documents Department
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The Drag of Airships : II - Drag of Bare Hulls

Description: "The extension of wind tunnel tests of models of airship hulls to full scale requires an extension from a VL of the order of less than 500 sq.ft./sec., to that of 80000 sq.ft./sec., where V = air speed, feet per second, L = length in feel of the particular form of hull. The reason for this research was to furnish the airship designer with a method for finding the VL curve of any conventional type of hull, using data obtained from actual performance of airships flown prior to 1926" (p. 1).
Date: October 1926
Creator: Havill, Clinton H.
Partner: UNT Libraries Government Documents Department
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Deflection of Propeller Blades While Running

Description: "The forces acting on the blades of a propeller proceed from the mass of the propeller and the resistance of the surrounding medium. The magnitude, direction and point of application of the resultant to the propeller blade is of prime importance for the strength calculation. Since it was obviously impracticable to bring any kind of testing device near the revolving propeller, not so much on account of the element of danger as on account of the resulting considerable disturbance of the air flow,… more
Date: October 1922
Creator: Katzmayr, R.
Partner: UNT Libraries Government Documents Department
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The Wing With a Pointed Tip

Description: In airplane construction generally one finds an almost exclusive use of wing tips that are practically square end but occasionally those with large rounded tips. For use as a cantilever wing, however, a wing with pointed tips may contain valuable aerodynamic advantages.
Date: October 1922
Creator: v. Prondzynski, Stephan
Partner: UNT Libraries Government Documents Department
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Effect of Periodic Changes of Angle of Attack on Behavior of Airfoils

Description: This report presents the results of a series of experiments, which gave some quantitative results on the effect of periodic changes in the direction of the relative air flow against airfoils. The first series of experiments concerned how the angle of attack of the wing model was changed by causing the latter to oscillate about an axis parallel to the span and at right angles to the air flow. The second series embraced all the experiments in which the direction of the air flow itself was periodi… more
Date: October 1922
Creator: Katzmayr, R.
Partner: UNT Libraries Government Documents Department
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Training of Aeronautical Engineers

Description: The requirements and preliminary coursework for aeronautical engineering are discussed. Some of the specific mechanical engineering properties that must be understood are provided. The report is incomplete.
Date: October 1922
Creator: Warner, Edward P.
Partner: UNT Libraries Government Documents Department
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Air Transport Economics

Description: Report presenting an exploration of the costs of operation for commercial airlines operating in Europe at the time of the report.
Date: October 1922
Creator: Warner, Edward P.
Partner: UNT Libraries Government Documents Department
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Computative examination of bending strength of girders originally curved and subjected to longitudinal compression

Description: This report examines the stipulation contained in the 1918 BLV, that a girder subjected to longitudinal compression under the influence of half of the specified breaking load, along with Euler bending safety with an initial deflection of 1/200 of the length of the girder can, at most, be subjected to half the stipulated breaking strength.
Date: October 1922
Creator: Hoff, Wilhelm
Partner: UNT Libraries Government Documents Department
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Calculation of the hull and of the car-suspension systems of airships

Description: Differential and integral curves are presented and well as numerous calculations relating to hulls. Some of the calculations include those relating to hulls, those relating to the invariability of the shape of the hulls, and those relating to the suspension of the hull.
Date: October 1924
Creator: Verduzio, R.
Partner: UNT Libraries Government Documents Department
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Mooring Airships

Description: The purpose of this paper is to summarize the present status of the problem of mooring airships. Mooring with one, two and even three cables are all discussed.
Date: October 1924
Creator: Crocco, G. A.
Partner: UNT Libraries Government Documents Department
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Duralumin, Its Properties and Uses

Description: A historical sketch of duralumin is presented, especially in regards to its manufacture by various countries. The properties of duralumin are discussed and strength characteristics listed. Increasing the hardness of duralumin by tempering is discussed as well as the uses of the metal.
Date: October 1924
Creator: Beck, R.
Partner: UNT Libraries Government Documents Department
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Results of Experiments With Slotted Wings

Description: This report recounts some of the successful experiments conducted in England and Germany on slotted wings and ailerons. Wind tunnel test results are given and examples of aircraft constructed with these new wing components are described.
Date: October 1924
Creator: Lachmann, G.
Partner: UNT Libraries Government Documents Department
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The Avro "Avian" Airplane: 65 HP. Armstrong-Siddeley "Genet" Engine

Description: The Avro Avian, designed by Mr. Chadwick of A.V. Roe & Co., Ltd. has a very low structural weight (estimated at 750 lbs. empty) but with sufficient structural integrity to be eligible of an "Aerobatics" certificate from the British Air Ministry. It can be configured as a monoplane, or a biplane with seaplane floats. It is designed for economical production.
Date: October 1926
Partner: UNT Libraries Government Documents Department
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Inherent Stability of Helicopters

Description: The equilibrium, in still air, of a "stationary" helicopter (i.e., of one having neither vertical nor translational velocity, but a tendency to remain practically motionless within restricted limits of space) presents some difficulty in practice and justifies a theoretical investigation of its "inherent stability," i.e., independent of the pilot.
Date: October 1923
Creator: Crocco, G. Arturo
Partner: UNT Libraries Government Documents Department
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Shortening the Landing Run

Description: Methods for shortening the landing run are discussed as well as the need for more emergency landing fields that will, by necessity, have to be short fields.
Date: October 1923
Creator: Warner, Edward P.
Partner: UNT Libraries Government Documents Department
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