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18,979 Matching Results
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Test of an Adjustable Pitch Model Propeller at Four Blade Settings
"This note describes tests of an adjustable blade metal model propeller, both in a free wind stream and in combination with a model fuselage, at four settings of the blades. The model propeller is designed for a uniform nominal pitch/diameter ratio of .7 and the blade settings used correspond to nominal pitch/diameter ratios of .5, .7, .9, and 1.1 at the .6 radius. The tests show that propellers of this type may be considerably changed in setting from the designed pitch angles and yet give excellent performance" (p. 1).
Date:
February 1930
Creator:
Lesley, E. P.
System:
The UNT Digital Library
The Pressure Distribution Over the Wings and Tail Surfaces of a PW-9 Pursuit Airplane in Flight
This report presents the results of an investigation to determine (1) the magnitude and distribution of aerodynamic loads over the wings and tail surfaces of a pursuit-type airplane in the maneuvers likely to impose critical loads on the various subassemblies of the airplane structure, (2) To study the phenomenon of center of pressure movement and normal force coefficient variation in accelerated flight, and (3) to measure the normal accelerations at the center of gravity, wing-tip, and tail, in order to determine the nature of the inertia forces acting simultaneously with the critical aerodynamic loads. The results obtained throw light on a number of important questions involving structural design.
Date:
February 3, 1930
Creator:
Rhode, Richard V.
System:
The UNT Digital Library
Strength of Welded Joints in Tubular Members for Aircraft
"The object of this investigation is to make available to the aircraft industry authoritative information on the strength, weight, and cost of a number of types of welded joints. This information will, also, assist the aeronautics branch in its work of licensing planes by providing data from which the strength of a given joint may be estimated. As very little material on the strength of aircraft welds has been published, it is believed that such tests made by a disinterested governmental laboratory should be of considerable value to the aircraft industry" (p. 323).
Date:
February 6, 1930
Creator:
Whittemore, H. L. & Brueggeman, W. C.
System:
The UNT Digital Library
Comparative flight performance with an NACA Roots supercharger and a turbocentrifugal supercharger
This report presents the comparative flight results of a roots supercharger and a turbocentrifugal supercharger. The tests were conducted using a modified DH-4M2 airplane. The rate of climb and the high speed in level flight of the airplane were obtained for each supercharger from sea level to the ceiling. The unsupercharged performance with each supercharger mounted in place was also determined. The results of these tests show that the ceiling and rate of climb obtained were nearly the same for each supercharger, but that the high speed obtained with the turbocentrifugal was better than that obtained with the roots. The high-speed performance at 21,000 feet was 122 and 142 miles per hour for the roots and turbocentrifugal, respectively.
Date:
February 25, 1930
Creator:
Schey, Oscar W. & Young, Alfred W.
System:
The UNT Digital Library
The aerodynamic characteristics of three tapered airfoils tested in the variable density wind tunnel
From Summary: "This report contains the lift, drag, and moment characteristics of tapered Clark Y, Gottingen 393, and USA 45 airfoils as obtained from tests made in the Variable Density Wind Tunnel of the NACA. The results are given at both low and high Reynolds Numbers to show scale effect and to provide data for use in airplane design."
Date:
February 1931
Creator:
Anderson, Raymond F.
System:
The UNT Digital Library
The Aerodynamic Wind Vane and the Inherent Stability of Airplanes
Report discussing the design of the wind vane described rests on the following line of reasoning: An airplane, originally in equilibrium about its C.G. is assumed to be deflected from this position through an angle (delta)i, the variation (delta)i being so sudden that the path of the C.G. and the airplane speed do not change while it is taking place. The aerodynamic forces acting on the wings, tail surfaces, fuselage, etc., which, as a whole, exerted a zero moment (M(sub G) = 0) about the center of gravity at the instant of equilibrium, now exert a moment M(sub G) not equal to 0.
Date:
February 1931
Creator:
Lapresle, A.
System:
The UNT Digital Library
The Amiot 140 M Military Airplane (French): An All-Metal Multiplace High-Wing Monoplane
Circular presenting the Amiot 140 M, which is the first of a series of airplanes that have been developed by a French aircraft manufacturer. A description of the design, dimensions, flight characteristics, blueprints, and photographs are provided.
Date:
February 1931
Creator:
unknown
System:
The UNT Digital Library
The Behavior of Conventional Airplanes in Situations Thought to Lead to Most Crashes
Simple flight tests were made on ten conventional airplanes for the purpose of determining their action in two situations, which are generally thought to precede and lead to a large proportion of airplane crashes. These situations are when in an attempt to stretch the glide in a forced landing, the airplane is stalled, and when while taking off, particularly if taking off steeply, the engine fails at a low altitude.
Date:
February 1931
Creator:
Weick, Fred E.
System:
The UNT Digital Library
Coal-Mine Fatalities in January, 1931
Report issued by the U.S. Bureau of Mines on the coal mine related deaths during the month of January, 1931. The number of fatalities and their causes are presented. This report includes tables.
Date:
February 1931
Creator:
Adams, William Waugh & Chenoweth, L.
System:
The UNT Digital Library
The Dewoitine D.30 Commercial Airplane (French): A High-Wing Cantilever Monoplane
Circular describing the Dewoitine D.30, which is a commercial high-wing cantilever monoplane. Details of the wing, fuselage, tail surfaces, landing gear, flight controls, electrical equipment, sending-receiving wireless installation, power plant, characteristics, performance, drawings, and photographs are provided.
Date:
February 1931
Creator:
unknown
System:
The UNT Digital Library
Flat Sheet Metal Girders With Very Thin Metal Web. Part 1: General Theories and Assumptions
The object of this report was to develop the structural method of sheet metal girders and should for that reason be considered solely from this standpoint. The ensuing methods were based on the assumption of the infinitely low stiffness in bending of the metal web. This simplifies the basis of calculations to such an extent that many questions of great practical importance can be examined which otherwise cannot be included in any analysis of the bending stiffness of the buckled plate. This report refers to such points as the safety in buckling of uprights to the effect of bending flexibility of spars, to spars not set parallel, etc.
Date:
February 1931
Creator:
Wagner, Herbert
System:
The UNT Digital Library
Flat Sheet Metal Girders With Very Thin Metal Web. Part 2: Sheet Metal Girders With Spars Resistant to Bending - Oblique Uprights - Stiffness
"Noting that the stiffness of the girder increases very rapidly as Beta increases, the result can be summed up as follows: When the cross stress preponderates in one direction and when the web plate is to be given the dimensions commensurate to its stresses, it is advisable (regardless of any ensuing structural difficulties) to set the uprights at about Beta = 120 degrees, thereby lowering the weight of the plate wall 15 percent (in contrast to Beta = 90 degrees), and raising the stiffness 55 percent. But, when the cross stresses alternate and are approximately of the same intensity in both directions, or, if the web plate thickness is determined by other structural reasons, then Beta = 90 degrees should be chosen" (p. 1).
Date:
February 1931
Creator:
Wagner, Herbert
System:
The UNT Digital Library
Flat Sheet Metal Girders With Very Thin Metal Web. Part 3: Sheet Metal Girders With Spars Resistant to Bending - the Stress in Uprights - Diagonal Tension Fields
This report continues the work presented in NACA-TM 605 and expands the scope to include the change in specific number of wrinkles from direction x to z, so that b and f become variable in direction z. Moreover, it seems likely that b and f increase from the edge toward the center if the sheet is infinitely thin.
Date:
February 1931
Creator:
Wagner, Herbert
System:
The UNT Digital Library
Interference effects and drag of struts on a monoplane wing
"Tests were conducted in the Variable Density Wind Tunnel of the NACA to determine the importance of the interference effects and drag of struts on a monoplane. Inclined struts were placed upon a Gottingen 387 airfoil in the lower surface positions and in two upper surface positions. Tests were made at values of Reynolds Number comparable with those obtained in flight. It was found that the interference drag of struts may be as great as the drag of the struts alone" (p. 1).
Date:
February 1931
Creator:
Ward, Kenneth E.
System:
The UNT Digital Library
Latécoère 38-0 Flying Boat (French): A Long-Range Sesquiplane for Carrying Mail
Report describing the Latécoère 38-0, which is a transatlantic mail seaplane. A description of the design, flight characteristics, and some of its special features is provided.
Date:
February 1931
Creator:
unknown
System:
The UNT Digital Library
Tests in the Variable Density Wind Tunnel to Investigate the Effects of Scale and Turbulence on Airfoil Characteristics
"The effect of scale and turbulence on the lift and drag of five airfoils the NACA 0006, the NACA 0021, the Clark Y and the USA 35-A, and the USN PS6, have been investigated in the Variable Density Wind Tunnel of the NACA. Tests were made over a wide scale range for only two different conditions of turbulence. Because of the limited scope of the tests, no general conclusions have been drawn, but it is indicated that increasing either turbulence or scale eliminates the discontinuities in the lift curves for thick airfoils, and that the effects of increased turbulence on the profile drag of airfoils tend to become of small importance at very high Reynolds Numbers" (p. 1).
Date:
February 1931
Creator:
Stack, John
System:
The UNT Digital Library
Torsion in box wings
From Summary: "Logical analysis of a box wing necessitates the allowance for the contribution of the drag spars to the torsional strength of the structure. A rigorous analysis is available in the use of the Method of Least Work. The best logical method of analysis is that applying Prandtl's Membrane Analogy. The results so obtained vary by a negligible amount from those obtained by the rigorous method."
Date:
February 1931
Creator:
Wheatley, John B.
System:
The UNT Digital Library
The Use of Elektron Metal in Airplane Construction
Memorandum presenting an evaluation of elektron, which is the lightest of the light metals and is of particular interest for aircraft construction. Some of its chemical properties, particular alloys and wrought materials that can be made using elektron, and some of the potential ways in which the material might be used are provided.
Date:
February 1931
Creator:
de Ridder, E. I.
System:
The UNT Digital Library
Investigation of the Diaphragm-Type Pressure Cell
"This report relates to various improvements in the process of manufacture of the NACA standard pressure cell. Like most pressure recording devices employing thin diaphragms, they would in general show considerable change in calibration with temperature and also some change of calibration with time or aging effect. The required diaphragm thickness and the desirable rate of mechanical magnification have been determined on the basis of several hundred tests" (p. 507).
Date:
February 3, 1931
Creator:
Theodorsen, Theodore
System:
The UNT Digital Library
The effect of valve timing upon the performance of a supercharged engine at altitude and an unsupercharged engine at sea level
This investigation was conducted to determine the comparative effects of valve timing on the performance of an unsupercharged engine at sea level and a supercharged engine at altitude. The tests were conducted on the NACA universal test engine. The timing of the four valve events was varied over a wide range; the engine speeds were varied between 1,050 and 1,500 r.p.m.; the compression ratios were varied between 4.35:1 and 7.35:1. The conditions of exhaust pressure and carburetor pressure of a supercharged engine were simulated for altitudes between 0 and 18,000 feet. The results show that optimum valve timing for a supercharged engine at an altitude of 18,000 feet differs slightly from that for an unsupercharged engine at sea level. A small increase in power is obtained by using the optimum timing for 18,000 feet for altitudes above 5,000 feet. The timing of the intake opening and exhaust closing becomes more critical as the compression ratio is increased.
Date:
February 4, 1931
Creator:
Schey, Oscar W. & Biermann, Arnold E.
System:
The UNT Digital Library
The vertical wind tunnel of the National Advisory Committee for Aeronautics
"The vertical open-throat wind tunnel of the National Advisory Committee for Aeronautics is described in this report. The tunnel was built mainly for studying the spinning characteristics of airplane models, but may be used as well for the usual types of wind-tunnel tests. A special spinning balance is being developed to measure the desired forces and moments with the model simulating the spin of an airplane. Satisfactory air flow has been attained with a velocity that is uniform over the jet to within plus or minus 0.5 per cent" (p. 499).
Date:
February 9, 1931
Creator:
Wenzinger, Carl J. & Harris, Thomas A.
System:
The UNT Digital Library
Airplane Flight in the Stratosphere
This brief survey of the problems encountered in high-altitude flight deals in particular with the need for high lift coefficient in the wings, large aspect ratios in the wings, and also the problem of hermetically sealing the cabin.
Date:
February 1932
Creator:
de Caria, Ugo
System:
The UNT Digital Library
Disintegration of a Liquid Jet
This report presents an experimental determination of the process of disintegration and atomization in its simplest form, and the influence of the physical properties of the liquid to be atomized on the disintegration of the jet. Particular attention was paid to the investigation of the process of atomization.
Date:
February 1932
Creator:
Haenlein, A.
System:
The UNT Digital Library
Effect of aging on taut rubber diaphragms
As part of an investigation of special compositions of rubber suitable for use as diaphragms for aircraft instruments, six samples were used as taut diaphragms in instruments and allowed to age for five years. Two of the instruments were in operating condition after this period of time and one had remarkably little change in performance. In making the rubber tetraethyl thorium disulfide was employed as a vulcanizing agent.
Date:
February 1932
Creator:
Strother, D. H. & Henrickson, H. B.
System:
The UNT Digital Library