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343 Matching Results
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The Influence of Wheel Spin-Up on Landing-Gear Impact
Note presenting an investigation of the influence of the wheel drag on the performance of the landing gear. The differential equations are developed and solved by numerical integration and by an analytical method. The possibilities of an eccentric wheel and an inclined shock strut are considered.
Date:
October 1954
Creator:
Flügge, W. & Coale, C. W.
System:
The UNT Digital Library
Effects of Wing Position and Horizontal-Tail Position on the Static Stability Characteristics of Models With Unswept and 45 Degree Sweptback Surfaces With Some Reference to Mutual Interference
Note presenting an investigation to determine the effects of wing position and horizontal-tail position on the low-speed static longitudinal and static lateral stability characteristics of airplane models with unswept and 45 degree sweptback surfaces. The results indicated that both the unswept and sweptback low-wing low-horizontal-tail configurations were the optimum configurations from the standpoint of longitudinal and lateral stability.
Date:
October 1951
Creator:
Goodman, Alex
System:
The UNT Digital Library
On the Attached Curved Shock in Front of a Sharp-Nosed Axially Symmetrical Body Placed in a Uniform Stream
Note presenting an investigation of the flow behind the attached curved shock near the nose of an axially symmetrical body placed in a uniform stream by considering the perturbations from the initial Taylor-Maccoll conical solution. Numerical results are obtained for the first-order perturbation equations, covering the cases with initial semivertex angle 10, 20 and 30 degrees, each at five different Mach numbers ranging approximately from the minimum one for an attached conical shock to a value around 5.
Date:
October 1951
Creator:
Shen, S. F. & Lin, C. C.
System:
The UNT Digital Library
Landing-Gear Impact
Report deals with the impact forces in landing gears. Both the landing impact and the taxiing impact have been considered, but drag forces have so far been excluded. The differential equations are developed and their numerical integration is shown, considering the nonlinear properties of the oleo shock strut. A way is shown for determining the dimensions of the metering pin from a given load-time diagram. A review of German literature on landing-gear impact is also presented.
Date:
October 1952
Creator:
Flügge, W.
System:
The UNT Digital Library
Generalized master curves for creep and rupture
Report presenting the similarity of Larson-Miller master curves for rupture life and minimum creep rate for aluminum, two aluminum alloys, two steels, and two high-temperature high-strength alloys. The approximate invariance of the product of rupture life and minimum creep rate is also shown for these materials.
Date:
October 1957
Creator:
Heimerl, George J. & McEvily, Arthur J., Jr.
System:
The UNT Digital Library
The Measurement of Pressure Altitude on Aircraft
Note presenting a determination of the accuracy with which pressure altitude can be measured by calculation of the errors in the measuring system, errors arising from operation of the system, and variations in atmospheric pressure. Some possibilities for reducing errors in the categories of altimeter-scale error, static-pressure error, atmospheric-reference error, flight technical error, friction error, and service error are provided.
Date:
October 1957
Creator:
Gracey, William
System:
The UNT Digital Library
Investigation of Some Mechanical Properties of Thermenol Compressor Blades
Note presenting a series of tests comparing the mechanical properties of similar compressor blades of AISI type 403 stainless steel and thermenol. Eighth-stage J47 and J65 compressor blades of each material were tested.
Date:
October 1957
Creator:
Johnson, Donald F.
System:
The UNT Digital Library
Motion of a ballistic missile angularly misaligned with the flight path upon entering the atmosphere and its effect upon aerodynamic heating, aerodynamic loads, and miss distance
From Summary: "An analysis is given of the oscillating motion of a ballistic missile which upon entering the atmosphere is angularly misaligned with respect to the flight path. The history of the motion for some example missiles is discussed from the point of view of the effect of the motion on the aerodynamic heating and loading. The miss distance at the target due to misalignment and to small accidental trim angles is treated. The stability problem is also discussed for the case where the missile is tumbling prior to atmospheric entry."
Date:
October 1957
Creator:
Allen, H. Julian
System:
The UNT Digital Library
Propellant vaporization as a criterion for rocket-engine design; Calculations using various log-probability distributions of heptane drops
Report presenting calculations made to determine the vaporization rates of fuel drops in a rocket engine for sprays having various log-probability distributions of n-heptane drops. The rates were calculated for various engine design and operating parameters. Results regarding the geometric standard deviation, mass-median drop size, variation in group size, and a correlation of results are provided.
Date:
October 1957
Creator:
Priem, Richard J.
System:
The UNT Digital Library
Heat transfer and boundary-layer transition on two blunt bodies at Mach numbers 3.12
Report presenting local heat-transfer parameters on a hemisphere-cone-cylinder and a 120 degree included angle cone-cylinder at a free stream Mach number 3.12 and at a range of Reynolds numbers.
Date:
October 1957
Creator:
Diaconis, N. S.; Wisniewski, Richard J. & Jack, John R.
System:
The UNT Digital Library
Effect of lubricant viscosity on rolling-contact fatigue life
Report presenting a series of rolling-contact fatigue tests conducted in a bench rig at the Lewis laboratory. Four paraffin-base mineral oils of varying viscosity were used as lubricants. A continuous trend toward longer lift was observed with increasing lubricant viscosity over the range studied.
Date:
October 1957
Creator:
Carter, Thomas L.
System:
The UNT Digital Library
Effect of Ground Proximity on the Aerodynamic Characteristics of a Four-Engine Vertical-Take-Off-and-Landing Transport-Airplane Model With Tilting Wing and Propellers
Note presenting an investigation to study the effect of ground proximity on the aerodynamic characteristics of a four-engine vertical-take-off-and-landing transport-airplane model with tilting wing and propellers. Tests were made with the wing at an angle of incidence of 90 degrees, the position used for vertical take-off or landing. Results regarding flow surveys and force tests are provided.
Date:
October 1957
Creator:
Newsom, William A., Jr.
System:
The UNT Digital Library
Theory and apparatus for measurement of emissivity for radiative cooling of hypersonic aircraft with data for Inconel and Inconel X
The importance of radiation as a means of cooling high-supersonic- and hypersonic-speed aircraft is discussed to show the need for measurements of the total hemispherical emissivity of surfaces. The theory underlying the measurement of the total hemispherical emissivity of surfaces is presented, readily duplicable apparatus for performing the measurements is described, and measurements for stably oxidized Inconel and Inconel X are given for the temperature range from 600 F to 2,000 F.
Date:
October 1957
Creator:
O'Sullivan, William J., Jr. & Wade, William R.
System:
The UNT Digital Library
External interference effects of a flow through static-pressure orifices of a NACA airspeed head at a Mach number of 3
Report presenting wind-tunnel testing to determine the static-pressure error resulting from external interference effects of flow through the static-pressure orifices of an NACA airspeed head at Mach number 3 and 0 degrees angle of attack. The results showed that the static-pressure error increased almost linearly with increase in mass flow through the orifices.
Date:
October 1957
Creator:
Silsby, Norman S.
System:
The UNT Digital Library
Rough-Water Impact-Load Investigation of a Chine-Immersed V-Bottom Model Having a Dead-Rise Angle of 10 Degrees
A hydrodynamic rough-water impact-loads investigation of a fixed-trim V-bottom float with a beam-loading coefficient of 5.78 and dead-rise angle of 10 degrees was made at the Langley impact basin. The size of the waves varied from approximately 10 to 60 feet in length and 1 to 2 feet in height. Time histories were obtained showing the position of the model relative to the wave throughout the impact and typical examples are presented. The load coefficient was found to vary primarily with the slope of the impacting wave.
Date:
October 1957
Creator:
Markey, Melvin F. & Carpini, Thomas D.
System:
The UNT Digital Library
Study of Pressure Distributions on Simple Sharp-Nosed Models at Mach Numbers From 16 to 18 in Helium Flow
Note presenting pressure distributions on some simple sharp-nosed aerodynamic shapes at Mach numbers from 16 to 18 in helium flow. The results obtained for the flat plate differ from the prediction of Lees for the strong interaction region by an amount which may be accounted for by the finite thickness of the leading edge. Results regarding the temperature recovery, schileren observations, and pressure distributions are provided.
Date:
October 1957
Creator:
Erickson, Wayne D.
System:
The UNT Digital Library
Weight-Strength Studies of Structures Representative of Fuselage Construction
Note presenting weight-strength plots for circular cylindrical shells in bending. The ring-stiffened shell, the longitudinally stiffened shell, and shells constructed of waffle-like or sandwich-type plates are compared in order to evaluate the effect of type of stiffening on bending strength, and shells of various materials are compared to evaluate the effect of material properties. The effect of shear loads on the bending strength of cylinders is considered.
Date:
October 1957
Creator:
Peterson, James P.
System:
The UNT Digital Library
A Method of Computing the Transient Temperature of Thick Walls From Arbitrary Variation of Adiabatic-Wall Temperature and Heat-Transfer Coefficient
Report presenting a method of calculating the temperature of thick walls using relatively new concepts like the time series and response to a unit triangle variation of surface temperature. It is particularly suitable for determining the wall temperature in one-dimensional thermal problems in aeronautics with a continuous variation of the heat-transfer coefficient and adiabatic-wall temperature.
Date:
October 1957
Creator:
Hill, P. R.
System:
The UNT Digital Library
Pressure Distribution and Damping in Steady Pitch at Supersonic Mach Numbers of Flat Swept-Back Wings Having All Edges Subsonic
Note presenting a method for calculating the pressure distribution and damping in steady pitch at supersonic Mach numbers of thin, flat, sweptback wings with all edges straight and subsonic. The two steps of the method are described and applied to wings with streamwise tips. The analysis showed that abrupt changes in pressure should occur along the various primary and reflected Mach lines on the wing, especially those originating at the tips of the leading edge.
Date:
October 1950
Creator:
Walker, Harold J. & Ballantyne, Mary B.
System:
The UNT Digital Library
Sintering mechanism between zirconium carbide and columbium
Report presenting an investigation of the sintering process and sintering mechanism of a zirconium carbide-columbium ceramal. Results regarding the study of the bonding specimen and study of the sintering specimens are provided.
Date:
October 1950
Creator:
Hamjian, H. J. & Lidman, William G.
System:
The UNT Digital Library
Wind-Tunnel Investigation at Low Speed of the Lateral Control Characteristics of an Unswept Untapered Semi-Span Wing of Aspect Ratio 3.13 Equipped With Various 25-Percent-Chord Plain Ailerons
Report presenting a wind-tunnel investigation at low speed to determine the lateral control characteristics of an unswept untapered semispan wing of aspect ratio 3.13 equipped with 25-percent-chord plain unsealed ailerons with various spans and spanwise locations. Results regarding wing aerodynamic characteristics and aileron control characteristics are provided.
Date:
October 1950
Creator:
Johnson, Harold S. & Hagerman, John R.
System:
The UNT Digital Library
Measurement of the moments of inertia of an airplane by a simplified method
Report presenting a simplified method for the experimental determination of the moments of inertia, product of inertia, and inclination of the principal axes, the associated equipment and techniques, and the application of this method to a conventional airplane.
Date:
October 1950
Creator:
Turner, Howard L.
System:
The UNT Digital Library
Effect of heat and power extraction on turbojet-engine performance 3: analytical determination of effects of shaft-power extraction
Report presenting an analysis of the performance of an axial-flow-type turbojet engine operating with shaft-power extraction by matching experimentally determined component characteristics of a typical axial-flow engine. General working charts are provided to investigate engine performance with variable and rated tail-pipe-nozzle area operation at constant turbine-inlet temperature, engine speed, and thrust.
Date:
October 1950
Creator:
Koutz, Stanley L.; Hensley, Reece V. & Rom, Frank E.
System:
The UNT Digital Library
Boundary-layer measurements in 3.84- by 10-inch supersonic channel
Report presenting boundary-layer measurements in the transonic and supersonic regions of a channel with maximum cross-sectional dimensions 3.84 by 10 inches and designed by potential-flow methods for a uniform Mach number of 2.08. Results regarding the Mach number distribution along the channel, temperature recovery and Prandtl number, boundary layer development, skin-friction coefficient, and secondary flows are provided.
Date:
October 1950
Creator:
Brinich, Paul F.
System:
The UNT Digital Library