Serial/Series Title
Country
States
1,181 Matching Results
Results open in a new window/tab.
Critical shear stress of infinitely long, simply supported plate with transverse stiffeners
From Summary: "A theoretical solution is given for the critical shear stress of an infinitely long, simply supported, flat plate with identical, equally spaced, transverse stiffeners of zero torsional stiffness. Results are obtained by means of the Lagrangian multiplier method and are presented in the form of design charts. Experimental results are included and are found to be in good agreement with the theoretical results."
Date:
April 1949
Creator:
Stein, Manuel & Fralich, Robert W.
System:
The UNT Digital Library
Reinforced Circular Cutouts in Plane Sheets
Note presenting an attempt to design the reinforcement of a cutout in a plane sheet in such a way that it is as nearly as possible equivalent to the part of the structure which has been cut out. A perfect equivalence would mean that the stresses and displacements of the structure remain the same as those which would have appeared without the cutout.
Date:
April 1949
Creator:
Reissner, H. & Morduchow, M.
System:
The UNT Digital Library
Effect of Increase in Afterbody Length on the Hydrodynamic Qualities of a Flying-Boat Hull of High Length-Beam Ratio
Report presenting an investigation to determine the effects of increased afterbody length on the hydrodynamic qualities of a model of a flying boat with a hull with a length-beam ratio of 15. Results regarding longitudinal stability, spray characteristics, excess thrust for take-off, landings in waves, and a summary chart are provided.
Date:
April 1949
Creator:
Kapryan, Walter J. & Clement, Eugene P.
System:
The UNT Digital Library
A Metallurgical Investigation of Large Forged Discs of Low-Carbon N-155 Alloy
Research was undertaken to ascertain the properties of better wrought heat resisting alloys in the form of large discs required for gas turbine rotors. The properties of large discs of low carbon N-155 alloy in both the as-forged and water-quenched and aged conditions were determined by means of stress-rupture and creep tests for time periods up to about 2000 hours at 1200, 1350, and 1500 F. Short-time tensile test, impact test, and time-total deformation characteristics are included.
Date:
April 1947
Creator:
Cross, Howard C. & Freeman, J. W.
System:
The UNT Digital Library
Effect of Catalysts and pH Strength of Resin-Bonded Plywood
Report presenting the effects of various catalysts used to cure resinous adhesives on the strength properties of plywood, especially in regard to the degree of solidity developed by the catalysts in the resin film and the plywood. Six resins were tested with birch wood, which is the most commonly used wood in aircraft construction.
Date:
April 1947
Creator:
Kline, G. M.; Reinhart, F. W.; Rinker, R. C. & De Lollis, N. J.
System:
The UNT Digital Library
Application of the Theory of Free Jets
Based upon Kirchoff's theory of free jets the flow through different screen arrangements of flat plates, as chiefly encountered with turbines in the cavitation zone is defined. It is shown by experiments that these theoretical results are very well representative in most cases of the conditions of discharge from water in air and consequently by cavitation. In addition, the experiments reveal a picture of the discrepancies between the actual flow and the theory of discharge of air in air (of water in water without cavitation).
Date:
April 1932
Creator:
Betz, A. & Petersohn, E.
System:
The UNT Digital Library
Aeromechanical Experimentation (Wind Tunnel Tests)
The following report endeavors to show that aeromechanical experimentation has become an important aid to theory. Experiments can be tried with separate parts of airplanes or with models of whole airplanes, with propellers, and with anything else that comes into contact with moving air.
Date:
April 1929
Creator:
Katzmayr, R.
System:
The UNT Digital Library
Fatigue of Internal Combustion Engines
Engine conditions such as pressure characteristics, temperatures, and mechanical fatigue enable the employment of a criterion of general fatigue which simultaneously takes account of both mechanical and thermal conditions, for the sake of comparing any projected engine with engines of the same type already in use.
Date:
April 1924
Creator:
Dumanois, P.
System:
The UNT Digital Library
Theoretical Investigation of the Effect of the Ailerons on the Wing of an Airplane
The present work investigates, on the basis of Prandtl's wing theory, the form of the lift distribution when the ailerons are deflected in opposite directions. An ideal fluid and a wing with a rectangular form are assumed. The moments must not cause any rotation of the wing or any deviation from the rectilinear motion.
Date:
April 1929
Creator:
Wieselsberger, C.
System:
The UNT Digital Library
Aerial photography : obtaining a true perspective
Report discussing a demonstration was given within the last few days at the British Museum by Mr. J. W. Gordon, author of "Generalized Linear Perspective" (Constable and Co.), a work describing a newly-worked-out system by which photographs can be made available for the purpose of exactly recording the dimensions of the objects photographed even when the objects themselves are presented foreshortened in the photograph.
Date:
April 1923
Creator:
United States. National Advisory Committee for Aeronautics.
System:
The UNT Digital Library
Steel Spars
A history of English metal spar construction is presented in this paper. The way in which different spar designs or spar materials influence the aircraft wing loading and aerodynamics is described.
Date:
April 1928
Creator:
Martin, Brian L.
System:
The UNT Digital Library
On the Definition of the Standard Atmosphere
"On April 15, 1920, the under Secretary of State for Aeronautics and Aerial Transport decided to adopt as Standard Atmosphere for official airplane tests in France, the atmosphere defined by the following law, known as the Law of the S.T.You.(Technical Section of Aeronautics): From 0 to 11,000 m. - 0=15-0.0065 Z and above 11,000 m. - 0= -56.5 degrees being the temperature in centigrade degrees at altitude Z expressed in meters. For altitude 0 the pressure is 760 mm of mercury. In the magazine "L'Aeronautique" Mr. A. Toussaint has already written at length on the first studies which led to the elaboration of this law. Since that time the results obtained have been confirmed by fuller and more abundant data which have justified the official adoption of the Law of the S.T.Ae" (p. 1).
Date:
April 1921
Creator:
Grimault, P.
System:
The UNT Digital Library
A Study of Curvilinear Flight
"When an airplane describes a curve it takes a certain time for it to turn from level to inclined position and then back to level again. In the following, we express the motion about the horizontal axis as "roll" or "bank" and the motion perpendicular to the vertical axis, i.e., the actual curve, as "turn." Equations and tables provide results on various aspects of turns, control settings, acceleration, inertia moments, and angular velocity" (p. 2).
Date:
April 1931
Creator:
Kruse, Helmuth
System:
The UNT Digital Library
Investigation of Certain Wing Shapes With Sections Varying Progressively Along the Span
This investigation has a double object: 1) the calculation of the general characteristics of certain wings with progressively varying sections; 2) the determination of data furnishing, in certain cases, some information on the actual distribution of the external forces acting on a wing. We shall try to show certain advantages belonging to the few wing types of variable section which we shall study and that, even if the general aerodynamic coefficients of these wings are not often clearly superior to those of certain wings of uniform section, the wings of variable section nevertheless have certain advantages over those of uniform section in the distribution of the attainable stresses.
Date:
April 1931
Creator:
Arsandaux, L.
System:
The UNT Digital Library
Aeronautical education and research at the Swiss Institute of Technology in Zurich
Progress in the scientific and practical fields of aviation has caused the Swiss Institute of Technology to organize lectures and practical training courses in all three branches of aeronautics and to found centers of scientific research, laboratories, etc., in order to supply the government and industries with scientifically and technically trained engineers.
Date:
April 1931
Creator:
Karner, L. & Ackeret, J.
System:
The UNT Digital Library
Safety Factors in Aviation
A formula for calculating the safety of airplanes is given and the stresses on airplane components are calculated. Some questions regarding the information obtained from the formula and its application to safe airplane design for pilots are provided.
Date:
April 1923
Creator:
Bleriot, Louis
System:
The UNT Digital Library
Development of Tailless and All-Wing Gliders and Airplanes
Tailless airplanes are characterized by having all their control surfaces, especially the elevator, incorporated in the wings. This paper provides a discussion of the history of their development and current state of development.
Date:
April 1932
Creator:
Lademann, Robert W. E.
System:
The UNT Digital Library
Wind-Tunnel Investigation at Low Speed of a Wing Having 63 Degree Sweepback and a Drooped Tip
From Summary: "The results of force tests made at low speed are presented to show the effect of longitudinal static stability produced by drooping the tip of a 63 degree sweptback wing. Five semispan wing models were tested: two incorporated curved drooped tips, two with abruptly drooped tips, and one without droop. The most favorable stability characteristics were measured for a model with an abruptly drooped tip, a fence, and a leading-edge flap; however, the use of these same auxiliary devices on the undrooped wing was nearly as effective."
Date:
April 7, 1955
Creator:
Blackaby, James R.
System:
The UNT Digital Library
Calculation of tab characteristics for flight conditions from wind-tunnel data
Report presenting tail-surface characteristics calculated from wind-tunnel data, which have been reported to not correspond with flight-test measurements. The primary problem under consideration is the calculation of the effect of tab deflection on the free-floating angle of the elevator, as in a servocontrol.
Date:
April 1942
Creator:
Sears, Richard I.
System:
The UNT Digital Library
Wind-Tunnel Investigation of Control-Surface Characteristics 16: Pressure Distribution Over an NACA 0009 Airfoil With 0.30-Airfoil-Chord Beveled-Trailing-Edge Flaps
Report discusses pressure-distribution tests of a plain flap with interchangeable beveled trailing edges on an NACA 0009 airfoil. The flap chord was 30 percent of the airfoil chord and the bevel chords were 15 and 20 percent of the flap chord. The purpose of these tests was to supply pressure-distribution data that may be used for structural and aerodynamic design of horizontal and vertical tail surfaces.
Date:
April 1944
Creator:
Hoggard, H. Page, Jr. & Bulloch, Marjorie E.
System:
The UNT Digital Library
Wind-tunnel investigation of control-surface characteristics 17: beveled-trailing-edge flaps of 0.20, 0.30, and 0.40 airfoil chord on an NACA 0009 airfoil
Report presenting force tests in two-dimensional flow in the 4- by 6-foot vertical tunnel to determine the aerodynamic characteristics of an NACA 0009 airfoil with flaps having chord at 3 locations of the airfoil chord and three degrees of the beveled trailing edges. The results indicated that, with a smooth leading edge, the increased trailing-edge angle on the flaps with sealed gaps decreased the slope of the control-fixed lift curve and the lift effectiveness.
Date:
April 1944
Creator:
Lockwood, Vernard E.
System:
The UNT Digital Library
Component Operating Trends During Acceleration and Deceleration of Two Hypothetical Two-Spool Turbojet Engines
Memorandum presenting an investigation of the compressor and turbine operating trends during acceleration and deceleration of two hypothetical two-spool turbojet engines. The two engines have the same component performance maps but the arbitrarily specified ratio of outer- to inner-spool moment of inertia for the second engine is 4 times that specified for the first engine. Results regarding the acceleration characteristics and deceleration characteristics are provided.
Date:
April 21, 1955
Creator:
Dugan, James F., Jr.
System:
The UNT Digital Library
An experimental investigation of two methods for reducing transonic drag of swept-wing and body combinations
Report presenting an investigation of a wing swept back 35 degrees in combination with one basic body and three modified bodies at a range of Mach numbers from 0.60 to 1.20. Results regarding force studies and pressure studies are provided. The bodies modified according to the Kuchenmann ring-vortex method resulted in superior aerodynamic characteristics except with regard to zero-lift drag at high supersonic Mach numbers.
Date:
April 29, 1955
Creator:
McDevitt, John B.
System:
The UNT Digital Library
Lift, drag, and static longitudinal stability characteristics of four airplane-like configurations at Mach numbers from 3.00 to 6.28
Report presenting lift, drag, and pitching-moment coefficients, lift-drag ratios, and center-of-pressure positions for four airplane-like configurations determined from tests at a range of Mach numbers and angles of attack. The wings and nose shapes were modified for each of the configurations.
Date:
April 25, 1955
Creator:
Neice, Stanford E.; Wong, Thomas J. & Hermach, Charles A.
System:
The UNT Digital Library