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An analysis of the power-off landing maneuver in terms of the capabilities of the pilot and the aerodynamic characteristics of the airplane
From Introduction: "In the present paper, an analysis of the power-off landing maneuver is presented in which an attempt is made to consider both the aerodynamic characteristics of the airplane and the human capabilities of the pilot. In this paper, the type of pilot judgment considered is that of a pilot with previous flight experience, although not necessarily flight experience in any particular airplane under discussion."
Date:
August 1953
Creator:
von Doenhoff, Albert E. & Jones, George W., Jr.
System:
The UNT Digital Library
Propeller-noise charts for transport airplanes
Report presenting calculations of rotational-noise and vortex-noise levels at a distance of 300 feet for engine ratings of 1000 to 10,000 horsepower for a large number of propellers in static operation. The results are presented in chart and table form for rapid estimation of the noise levels and spectrums in a range of tip Mach numbers. Results regarding tip Mach number, number of blades, and power loading are provided.
Date:
June 1953
Creator:
Hubbard, Harvey H.
System:
The UNT Digital Library
Direct-reading design charts for 24S-T3 aluminum-alloy flat compression panels having longitudinal formed hat-section stiffeners and comparisons with panels having Z-section stiffeners
Report presenting direct-reading design charts for 24S-T3 aluminum-alloy flat compression panels with longitudinal formed hat-section stiffeners. The charts make it possible to directly determine the stress and all panel proportions required to carry a given intensity of loading with a given skin thickness and effective length of panel. Results regarding simple compression, combined compression and bending, and combined compression, bending, and shear are provided.
Date:
March 1953
Creator:
Hickman, William A. & Dow, Norris F.
System:
The UNT Digital Library
A Rapid Method for Use in Design of Turbines Within Specified Aerodynamic Limits
Note presenting a method for the rapid determination of design velocity diagrams of turbine stages within specified aerodynamic limits. The method is presented in both chart and tabular form.
Date:
April 1953
Creator:
Cavicchi, Richard H. & English, Robert E.
System:
The UNT Digital Library
An application of the method of characteristics to two-dimensional transonic flows with detached shock waves
From Summary: "An application of the method of characteristics is presented which affords a means for determining the surface pressures for a class of two-dimensional airfoils of given nose shape and arbitrary rear part in a sonic or supersonic stream if surface pressure data are given for one member of the class. For engineering purposes, the method of characteristics may be replaced by a simple application of Prandtl-Meyer flow concepts. An explanation of the nonlinear force characteristics of two-dimensional airfoils at transonic speeds is presented on the basis of sensitivity of these flows to changes in geometry and angle of attack."
Date:
March 1953
Creator:
Harder, Keith C. & Klunker, E. B.
System:
The UNT Digital Library
A Low-Speed Experimental Study of the Directional Characteristics of a Sharp-Nosed Fuselage Through a Large Angle-of-Attack Range at Zero Angle of Sideslip
Static yawing moments and some instantaneous yawing moments are presented through a range of angle of attack at zero sideslip angle for a plain fuselage model having a sharp conical nose and for the fuselage with several nose modifications, one of which consisted of a ring located at different stations along the nose. Some circumferential pressure measurements at one station on the body at several angles of attack are also presented.
Date:
March 1953
Creator:
Letko, William
System:
The UNT Digital Library
Analytical investigation of icing limit for diamond-shaped airfoil in transonic and supersonic flow
From Introduction: "The results presented herein were calculated for a symmetrical diamond airfoil at zero angle of attack for a range of airfoil-thickness ratios from 0.02 to 0.10, pressure altitude from sea level to 45,000 feet, and free-stream static temperatures to -.40^o F."
Date:
January 1953
Creator:
Callaghan, Edmund E. & Serafini, John S.
System:
The UNT Digital Library
On the Development of Turbulent Wakes from Vortex Streets
"Wake development behind circular cylinders at Reynolds numbers from 40 to 10,000 was investigated in a low-speed wind tunnel. Standard hotwire techniques were used to study the velocity fluctuations. The Reynolds number range of periodic vortex shedding is divided into two distinct subranges. At R = 40 to 150, called the stable range, regular vortex streets are formed and no turbulent motion is developed" (p. 1).
Date:
March 1953
Creator:
Roshko, Anatol
System:
The UNT Digital Library
Effect of processing variables on the transition temperature, strength, and ductility of high-purity, sintered, wrought molybdenum metal
Report presenting an investigation of the effect of processing variables on the properties of sintered, wrought molybdenum. The amount of swaging, recrystallization, and stress-relieving were considered.
Date:
March 1953
Creator:
Dike, Kenneth C. & Long, Roger A.
System:
The UNT Digital Library
Effect of thermal properties on laminar-boundary-layer characteristics
Report presenting an iteration method for solving the laminar-boundary-layer equations for compressible flow in the absence of a pressure gradient when the temperature variation of all the fluid thermal properties is considered. Results in regard to skin friction and heat-transfer characteristics are provided.
Date:
March 1953
Creator:
Klunker, E. B. & McLean, F. Edward
System:
The UNT Digital Library
The Condensation Line of Air and the Heats of Vaporization of Oxygen and Nitrogen
"The condensation pressure of air was determined over the range of temperature from 60 to 85 K. The experimental results were slightly higher than the calculated values based on the ideal solution law. Heat of vaporization of oxygen was determined at four temperatures ranging from about 68 to 91 K and of nitrogen similarly at four temperatures ranging from 62 to 78 K" (p. 1).
Date:
June 1953
Creator:
Furukawa, George T. & McCoskey, Robert E.
System:
The UNT Digital Library
Behavior of materials under conditions of thermal stress
Report presenting a review of available information on the behavior of brittle and ductile materials under conditions of thermal stress and thermal shock. A number of practical methods that have been used to minimize the negative effects of thermal stress and shock are provided.
Date:
July 1953
Creator:
Manson, S. S.
System:
The UNT Digital Library
A Modified Reynolds Analogy for the Compressible Turbulent Boundary Layer on a Flat Plate
Note presenting a modified Reynolds analogy developed for the compressible turbulent boundary layer on a flat plate. When mixing-length theories are used to evaluate terms of the final expressions, it is found for air that the ratio of Stanton number to half the local skin-friction coefficient is greater than unity.
Date:
March 1953
Creator:
Rubesin, Morris W.
System:
The UNT Digital Library
Physical Properties of Concentrated Nitric Acid
Note presenting a review of the data existing in the literature and experimental measurements made in order to obtain the physical properties of white fuming nitric acid. The main object of the investigation was to obtain reliable values of the thermal properties of concentrated nitric acid for use in correlating the data obtained in heat-transfer research and in fluid-friction-characteristics investigations.
Date:
June 1953
Creator:
Sibbitt, W. L.; St. Clair, C. R.; Bump, T. R.; Pagerey, P. F.; Kern, J. P. & Fyfe, D. W.
System:
The UNT Digital Library
Studies of the use of Freon-12 as a wind tunnel testing medium
Report presenting a comparison of studies relating to the use of Freon-12 as a substitute medium for air in aerodynamic testing and methods for predicting the aerodynamic characteristics of bodies in air. The Freon charging and recovery system for the Langley low-turbulence pressure tunnel is described.
Date:
August 1953
Creator:
von Doenhoff, Albert E.; Braslow, Albert L. & Schwartzberg, Milton A.
System:
The UNT Digital Library
Relation Between Roughness of Interface and Adherence of Porcelain Enamel to Steel
Note presenting porcelain-enamel ground coats, which were prepared and applied under conditions that gave various degrees of adherence between enamel and a low-carbon steel. This study was primarily undertaken to find out additional information on the mechanism of adherence of porcelain-enamel ground coats to iron.
Date:
April 1953
Creator:
Richmond, J. C.; Moore, D. G.; Kirkpatrick, H. B. & Harrison, W. N.
System:
The UNT Digital Library
A Study of the Application of Power-Spectral Methods of Generalized Harmonic Analysis to Gust Loads on Airplanes
Note presenting an examination of the applicability of some results from the theory of generalized harmonic analysis (or power-spectral analysis) to the analysis of gust loads on airplanes in continuous rough air. The general relations for linear systems between power spectrums of a random input disturbance and an output response are used to relate the spectrum of airplane load in rough air to the spectrum of atmospheric gust velocity.
Date:
January 1953
Creator:
Press, Harry & Mazelsky, Bernard
System:
The UNT Digital Library
The calculation of pressure on slender airplanes in subsonic and supersonic flow
"Under the assumption that a wing, body, or wing-body combination is slender or flying at near sonic velocity, expressions are given which permit the calculation of pressure in the immediate vicinity of the configuration. The disturbance field, in both subsonic and supersonic flight, is shown to consist of two-dimensional disturbance fields extending laterally and a longitudinal field that depends on the streamwise growth of cross-sectional area. A discussion is also given of couplings, between lifting and thickness effects, that necessarily arise as a result of the quadratic dependence of pressure on the induced velocity components" (author).
Date:
March 1953
Creator:
Heaslet, Max A. & Lomax, Harvard
System:
The UNT Digital Library
Water-landing investigation of a flat-bottom v-step model and comparison with a theory incorporating planing data
Report presenting testing of a flat-bottom V-step model with a beam loading of 4.6 subjected to fixed-trim impacts in smooth water. Testing occurred at three different trim angles and a range of initial flight-path angles. Data were obtained as time histories of draft, vertical velocity, and vertical acceleration. The results are presented as plots of nondimensional lift, draft, vertical velocity, and time against flight-path angle at contact.
Date:
May 1953
Creator:
Miller, Robert W.
System:
The UNT Digital Library
Impingement of water droplets on a cylinder in an incompressible flow field and evaluation of rotating multicylinder method for measurement of droplet-size distribution, volume-median droplet size, and liquid-water content in clouds
Report presenting an evaluation of the rotating multicylinder method for the measurement of droplet-size distribution, volume-median droplet size, and liquid-water content in clouds, which showed that small uncertainties in the basic data eliminate the distinction between cloud droplet-size distributions and are a source of large errors in the determination of droplet size. Matching curves for obtaining droplet-size distribution, volume-median droplet size, and liquid-water content from flight data were computed from the results of the droplet-trajectory configurations.
Date:
March 1953
Creator:
Brun, Rinaldo J. & Mergler, Harry W.
System:
The UNT Digital Library
An analysis of the factors affecting the loss in lift and shift in aerodynamic center produced by the distortion of a swept wing under aerodynamic load
From Introduction: "The importance of this aeroelastic phenomenon has been recognized for some time, and several investigators have developed more or less refined methods for analysis of wing elastic distortions and their effects. (For examples, see refs. 1 to 4.) More specific evidence as to the influence of wing external geometry (in conjunction with flight condition) on this flexibility-longitudinial-stability problem would appear to be of interest to the aerodynamicist, however, so that he can obtain rough indications as to which wing plan forms would be practical from aeroelastic considerations."
Date:
March 1953
Creator:
Mathews, Charles W. & Kurbjun, Max C.
System:
The UNT Digital Library
Strength analysis of stiffened thick beam webs with ratios of web depth to web thickness of approximately 60
"The results of an experimental investigation of the strength of plane diagonal-tension webs with ratios of web depth to web thickness of about 60 are presented. An analysis of the beam indicated that the methods of strength analysis presented in NACA TN 2661 are applicable to beams with flanges symmetrically arranged with respect to the web if the portal-frame effect is taken into account" (p. 1).
Date:
May 1953
Creator:
Levin, L. Ross
System:
The UNT Digital Library
Matrix methods for determining the longitudinal-stability derivatives of an airplane from transient flight data
Report presenting three matrix methods for determining the longitudinal-stability derivatives from transient flight data. The results obtained for the methods presented depend in a large measure on accurate instrument measurements and require considerable computation to yield adequate engineering answers.
Date:
March 1953
Creator:
Donegan, James J.
System:
The UNT Digital Library
Effects of Parallel-Jet Mixing on Downstream Mach Number and Stagnation Pressure With Application to Engine Testing in Supersonic Tunnels
"A one-dimensional analysis of the results of the parallel-jet mixing encountered in the testing of engines in supersonic wind tunnels is reported. Equations were derived for determining the totla pressure and Mach number behind the tunnel terminal shock. The method represents a simple procedure for determining these quantities while a tunnel is still in the design stage" (p. 1).
Date:
March 1953
Creator:
Bernstein, Harry
System:
The UNT Digital Library