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Stress-life Relation of the Rolling-contact Fatigue Spin Rig

Stress-life Relation of the Rolling-contact Fatigue Spin Rig PDF Author: Robert H. Butler
Publisher:
ISBN:
Category : Ball-bearings
Languages : en
Pages : 30

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Book Description
The rolling-contact fatigue spin rig was used to test groups of SAE 52100 9.16-inch-diameter balls lubricated with a mineral oil at 600,000-, 675,000-, and 750,000-psi maximum Hertz stress. Cylinders of AISI M-1 vacuum and commercial melts and MV-1 (AISI M-50) were used as race specimens. Stress-life exponents produced agree closely with values accepted in industry. The type of failure obtained in the spin rig was similar to the subsurface fatigue spells found in bearings.

Technical Note - National Advisory Committee for Aeronautics

Technical Note - National Advisory Committee for Aeronautics PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1030

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A Study of Some Factors Affecting Rolling-contact Fatigue Life

A Study of Some Factors Affecting Rolling-contact Fatigue Life PDF Author: Thomas L.. Carter
Publisher:
ISBN:
Category : Lubrication and lubricants
Languages : en
Pages : 56

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Effect of Hardness and Other Mechanical Properties on Rolling-contact Fatigue Life of Four High-temperature Bearing Steels

Effect of Hardness and Other Mechanical Properties on Rolling-contact Fatigue Life of Four High-temperature Bearing Steels PDF Author: Thomas L. Carter
Publisher:
ISBN:
Category : Ball-bearings
Languages : en
Pages : 58

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Effect of Propeller Location and Flap Deflection on the Aerodynamic Characteristics of a Wing-propeller Combination for Angles of Attack from 0 to 80 Degrees

Effect of Propeller Location and Flap Deflection on the Aerodynamic Characteristics of a Wing-propeller Combination for Angles of Attack from 0 to 80 Degrees PDF Author: William A. Newsom
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 714

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Book Description
An investigation has been made to determine the effect of propeller location and flap deflection on the lift, drag, and pitching-moment characteristics of a wing-propeller combination over an angle-of-attack range from 0 to 80 degrees. The model had four propellers, the slipstream from which covered practically the entire span of the wing. The wing had a 30-percent-chord slotted flap and an 8.5-percent-chord slat. Data were obtained for flap deflections of 0, 20, 40, and 60 degrees with the slat off and on. For one propeller position the power input to the model was measured and tuft studies of the flow on the wing were made. The data are analyzed to assess the feasibility, from consideration of stability and control, of a tilting-wing vertical-take-off-and-landing airplane with the wing pivoted behind the primary wing structure to provide a desirable structural configuration. The main object of the investigation was to determine whether advantage might be taken of the forward shift of the center of gravity of the airplane, as the wing is tilted from an angle of attack of 90 to 0 degrees, to minimize the change in trim pitching moment throughout the transition speed range for such a configuration. The results indicate that with proper propeller position and programming of flap deflection, it is possible to design a configuration of this type in which essentially no change in trim is required throughout the transition from hovering to normal unstalled forward flight.

Preliminary Studies of Rolling-contact Fatigue Life of High-temperature Bearing Materials

Preliminary Studies of Rolling-contact Fatigue Life of High-temperature Bearing Materials PDF Author: Thomas L. Carter
Publisher:
ISBN:
Category : Bearings (Machinery)
Languages : en
Pages : 32

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Book Description
A preliminary investigation of the of rolling-contact fatigue life of both races and balls of some promising high-temperature bearing materials were made at room temperature in the rolling-contact fatigue spin rig.

Preliminary Metallographic Studies of Ball Fatigue Under Rolling-contact Conditions

Preliminary Metallographic Studies of Ball Fatigue Under Rolling-contact Conditions PDF Author: H. Robert Bear
Publisher:
ISBN:
Category : Ball-bearings
Languages : en
Pages : 48

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Book Description
The metallurgical results produced on balls tested in the rolling-contact fatigue spin rig were studied by metallographic examination. Origin and progression of fatigue failures were observed. These evaluations were made on SAE 52100 and AISI M-1 balls fatigue tested at room temperature (80 F) and 200 to 250 F. Most failures originated subsurface in shear; inclusions, structure changes, and directionalism adversely affected ball fatigue life. Structures in the maximum-shear-stress region of the balls of both materials were stable at room temperature and unstable at 200 to 250 F. Failures were of the same type as those found in full-scale bearings.

NASA Technical Report

NASA Technical Report PDF Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 60

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Advanced Bearing Technology

Advanced Bearing Technology PDF Author: Edmond E. Bisson
Publisher:
ISBN:
Category : Bearings (Machinery)
Languages : en
Pages : 524

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Approximations for the Thermodynamic and Transport Properties of High-temperature Air

Approximations for the Thermodynamic and Transport Properties of High-temperature Air PDF Author: C. Frederick Hansen
Publisher:
ISBN:
Category : Air
Languages : en
Pages : 722

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Book Description
The thermodynamic and transport prorerties of high-temperature air are found in closed form starting from approximate partition functions for the major components in air and neglecting all minor components. The compressibility, energy, entropy, the specific heats, the speed of sound, the coefficients of viscosity and of thermal conductivity, and the Prandtl numbers for air are tabulated from 500 degrees to 15,000 degrees K over a range of pressure from 0.0001 to 100 atmospheres. The enthalpy of air and the mol fractions of the major components of air can easily be found from the tabulated values for compressibility and energy. It is predicted that the Prandtl number for fully ionized air will become small compared to unity, the order of 0.01, and this implies that boundary layers in such flow will be very transparent to heat flux.