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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

Wind Tunnel Tests on Airfoil Boundary Control Using a Backward Opening Slot

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

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 the air flowed out of the slot rather than in through it, and in consequence, the maximum lift coefficient was decreased" (p. 1).
Date: October 1929
Creator: Bamber, Millard J.
Partner: UNT Libraries Government Documents Department

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

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

Wind tunnel pressure distribution tests on a series of biplane wing models Part 2: 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 wings.
Date: October 1929
Creator: Knight, Montgomery & Noyes, Richard W.
Partner: UNT Libraries Government Documents Department

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

Experiments With a Wing Model From Which the Boundary Is Removed by Suction

Description: The present report deals with a series of tests made for the purpose of improving flow conditions about wings by applying the suction principle (increase of the lift coefficient and reduction of the drag about very thick wing sections). Though not conclusive, the report contains interesting results.
Date: October 1929
Creator: Schrenk, Oskar
Partner: UNT Libraries Government Documents Department

Effect of variation of chord and span of ailerons on rolling and yawing moments at several angles of pitch

Description: This report presents the results of an extension to higher angles of attack of the investigation of the rolling and yawing moments due to ailerons of various chords and spans on two airfoils having the Clark Y and U. S. A. 27 wings. The measurements were made at various angles of pitch but at zero angle of roll and yaw, the wing chord being set at an angle of +4 degrees to the fuselage axis. In the case of the Clark Y airfoil the measurements have been extended to a pitch angle of 40 degrees, using ailerons of span equal to 67 per cent of the wing semispan and chord equal to 20 and 30 per cent of the wing chord. The work was conducted on wing models of 60-inch span and 10-inch chord.
Date: October 7, 1929
Creator: Heald, R. H.; Strother, D. H. & Monish, B. H.
Partner: UNT Libraries Government Documents Department

Large-scale aerodynamic characteristics of airfoils as tested in the variable density wind tunnel

Description: From Summary: "In order to give the large-scale characteristics of a variety of airfoils in a form which will be of maximum value, both for airplane design and for the study of airfoil characteristics, a collection has been made of the results of airfoil tests made at full-scale values of the Reynolds number in the variable density wind tunnel of the National Advisory Committee for Aeronautics. They have been corrected for tunnel wall interference and are presented not only in the conventional form but also in a form which facilitates the comparison of airfoils and from which corrections may be easily made to any aspect ratio. An example showing the method of correcting the results to a desired aspect ratio has been given for the convenience of designers. In addition, the data have been analyzed with a view to finding the variation of the aerodynamic characteristics of airfoils with their thickness and camber."
Date: October 21, 1929
Creator: Jacobs, Eastman N. & Anderson, Raymond F.
Partner: UNT Libraries Government Documents Department

The A. B. Flygindustri "K 37" (Swedish Junkers): A Low-Wing All-Metal Military Airplane

Description: Report discusses the characteristics of the K 37 all-metal long-wing monoplane and its use for long-distance scouting, as a day bomber, and as a heavy fighting airplane. Its engines, climbing capacity, action radius, bombing installation, fuselage, controls, and landing gear are explored in depth.
Date: October 1929
Creator: United States. National Advisory Committee for Aeronautics.
Partner: UNT Libraries Government Documents Department

Fire prevention on airplanes. Part 2

Description: This part of the report presents a detailed examination of spark prevention, fire extinguishers, and fuel tank location and design. A continued program of investigations and research is also proposed.
Date: October 1929
Creator: Sabatier, J.
Partner: UNT Libraries Government Documents Department

Fire prevention on airplanes. Part 1

Description: Various methods for preventing fires in airplanes are presented with most efforts centering around prevention of backfires, new engine and carburetor designs, as well as investigations on different types of fuels.
Date: October 1929
Creator: Sabatier, J.
Partner: UNT Libraries Government Documents Department

Handley Page Metal Construction

Description: In this report Handley Page construction techniques are shown such as: solid-drawn tubular duralumin spars are used in the stabilizer; plain channel sections are used extensively for minor components; and the manner of assembling them into a stabilizer compression strut is shown.
Date: October 1929
Partner: UNT Libraries Government Documents Department