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Results 15371 - 15380 of 17,147
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Farman two-engine commercial biplane F.180 (French)

Farman two-engine commercial biplane F.180 (French)

Date: October 1, 1929
Creator: unknown
Description: The F180 was designed for reliable long distance travel in stages of 500, 1000, 1500 km, carrying loads of 2500, 2000, and 1500 kg respectively. At maximum load it can carry 20 passengers.
Contributing Partner: UNT Libraries Government Documents Department
Fire prevention on airplanes. Part I

Fire prevention on airplanes. Part I

Date: October 1, 1929
Creator: Sabatier, J
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.
Contributing Partner: UNT Libraries Government Documents Department
Fire prevention on airplanes. Part II

Fire prevention on airplanes. Part II

Date: October 1, 1929
Creator: Sabatier, J
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.
Contributing Partner: UNT Libraries Government Documents Department
Handley Page metal construction

Handley Page metal construction

Date: October 1, 1929
Creator: unknown
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.
Contributing Partner: UNT Libraries Government Documents Department
The impact on seaplane floats during landing

The impact on seaplane floats during landing

Date: October 1, 1929
Creator: Von Karman, TH
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.
Contributing Partner: UNT Libraries Government Documents Department
Information obtained from airplane flight tests in the year 1927-1928

Information obtained from airplane flight tests in the year 1927-1928

Date: October 1, 1929
Creator: Hubner, W
Description: The information obtained from flight tests in 1927-1928 covers chiefly the effect of the structural features of an airplane on its stability, controllability, maneuverability and spinning characteristics.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel pressure distribution tests on a series of biplane wing models Part II : effects of changes in decalage, dihedral, sweepback and overhang

Wind tunnel pressure distribution tests on a series of biplane wing models Part II : effects of changes in decalage, dihedral, sweepback and overhang

Date: October 1, 1929
Creator: Knight, Montgomery & Noyes, Richard W
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.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel pressure distribution tests on an airfoil with trailing edge flap

Wind tunnel pressure distribution tests on an airfoil with trailing edge flap

Date: October 1, 1929
Creator: Wenzinger, Carl J & Loeser, Oscar
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.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests on airfoil boundary control using a backward opening slot

Wind tunnel tests on airfoil boundary control using a backward opening slot

Date: October 1, 1929
Creator: Knight, Montgomery & Bamber, Millard J
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. The greatest increase in maximum lift was 96 per cent, the greatest decrease in minimum drag was 27 per cent, and the greatest increase in the ratio, maximum lift coefficient/minimum drag coefficient, was 151 per cent.
Contributing Partner: UNT Libraries Government Documents Department
Wind tunnel tests on an airfoil equipped with a split flap and a slot

Wind tunnel tests on an airfoil equipped with a split flap and a slot

Date: October 1, 1929
Creator: Bamber, Millard J
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.
Contributing Partner: UNT Libraries Government Documents Department