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A Rosette Strain Computer

Description: Note presenting a description of an electrical apparatus that serves as a computer for the evaluation of linear strain measurements taken in rosette fashion on the surface of a structural element carrying tension or compression and shear. The solution of the strain circle is accomplished by coupled rotary transformers, one representing each of the rosette gages.
Date: December 1942
Creator: Klemperer, W. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Problems Concerning the Stability and Maneuverability of Airplanes

Description: "The stability of an airplane can be easily determined by wind-tunnel tests, especially by simple tests with models mounted wind-vane fashion. However, each stability curve plotted by this method is valid only for a certain setting of the corresponding control surface, i.e., it characterizes the stability of the airplane with the control stick in a given position. The problems thus defined are studied from the point of view of longitudinal and transverse stability. Directional stability is not … more
Date: March 1932
Creator: Biche, Jean
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On the Contribution of Turbulent Boundary Layers to the Noise Inside a Fuselage

Description: "The following report deals in preliminary fashion with the transmission through a fuselage of random noise generated on the fuselage skin by a turbulent boundary layer. The concept of attenuation is abandoned and instead the problem is formulated as a sequence of two linear couplings: the turbulent boundary layer fluctuations excite the fuselage skin in lateral vibrations and the skin vibrations induce sound inside the fuselage. The techniques used are those required to determine the response … more
Date: December 1956
Creator: Corcos, G. M. & Liepmann, H. W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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An Investigation of Loads on Ailerons at Transonic Speeds

Description: "Some aileron load characteristics for three thin wings varying in sweep have been presented for Mach numbers from 0.80 to 1.05. For the transonic Mach number range, shock effects exert a large influence on the loading, but the exact location of each shock for a specific wing design cannot be cataloged at the present time. It is shown, however, that the aileron loading, although greater in magnitude than at subsonic speeds, nevertheless varies in as uniform a fashion as at subsonic speeds" (p. … more
Date: May 27, 1955
Creator: Runckel, Jack F. & Gray, W. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Analysis of the Creep Behavior of a Square Plate Loaded in Edge Compression

Description: From Introduction: "In reference 1 results of creep tests and empirical method for predicting collapse times are presented for plates loaded in compression on two opposite edges and with the remaining edges unloaded and supported in V-groove fixtures. Other approximate methods for handling plates having types of edge support are suggested in reference 2; however, experimental verification for these methods is quite limited. In reference 3 an analysis based on small-deflection theory is made of … more
Date: September 1958
Creator: McComb, Harvey G., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Determination of elastic stresses in gas-turbine disks

Description: A method is presented for the calculation of elastic stresses in symmetrical disks typical of those of a high-temperature gas turbine. The method is essentially a finite-difference solution of the equilibrium and compatibility equations for elastic stresses in a symmetrical disk. Account can be taken of point-to-point variations in disk thickness, in temperature, in elastic modulus, in coefficient of thermal expansion, in material density, and in Poisson's ratio. No numerical integration or tri… more
Date: 1947
Creator: Manson, S. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Motion of the Two-Control Airplane in Rectilinear Flight After Initial Disturbances With Introduction of Controls Following an Exponential Law

Description: "An airplane in steady rectilinear flight was assumed to experience an initial disturbance in rolling or yawing velocity. The equations of motion were solved to see if it was possible to hasten recovery of a stable airplane or to secure recovery of an unstable airplane by the application of a single lateral control following an exponential law. The sample computations indicate that, for initial disturbances complex in character, it would be difficult to secure correlation with any type of expon… more
Date: September 1937
Creator: Klemin, Alexander
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Airplane Parachutes

Description: The "Bulletin Technique", of March, 1919, gave the results of tests and studies made up to that date in connection with airplane parachutes. This work has been continued.
Date: August 1925
Creator: Mazer
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Flat Wing With Sharp Edges in a Supersonic Stream

Description: A basic treatment is given for the approximate solution of the problem of two-dimensional supersonic flow past a thin wing at small angles of attack. The pressure distribution at the surface, the lifting force, and the wave drag are determined.
Date: March 1956
Creator: Donov, A. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Observations on the Maximum Average Stress of Flat Plates Buckled in Edge Compression

Description: Note presenting compressive-strength data on flat plates for a number of aircraft structural materials subjected to graphical study. Results indicated that the maximum average stress, in the region where it differs appreciably from the critical stress, could be expressed as a constant times the one-fourth power of the critical stress times the three-fourths power of the compressive yield stresses.
Date: February 1949
Creator: Schuette, E. H.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The application of matrix methods to coordinate transformations occurring in systems studies involving large motions of aircraft

Description: Report presenting the method and advantages of matrix algebra in setting up the geometric aspects of problems of airplane motion. The paper is divided into two parts. The first is about the aspects of matrix algebra required for use in orthogonal transformations and the other shows how to use orthogonal transformations in matrix form by applying them in several examples.
Date: May 1957
Creator: Doolin, Brian F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Formation and Combustion of Smoke in Laminar Flames

Description: "The nature and formation of smoke and its combustion were investigated. Smoke, which consist of tiny mesomorphous crystals tightly packed into popcorn-ball-like particles that agglomerate to give filaments, was found to contain about 5 percent of the hydrogen originally present in the fuel. Factors affecting smoke formation were studied in both diffusion flames and premixed Bunsen flames. It is suggested that smoking tendency increases with increasing stability of the carbon skeleton of the mo… more
Date: August 17, 1954
Creator: Schalla, Rose L.; Clark, Thomas P. & McDonald, Glen E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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A Method of Shear-Lag Analysis of Box Beams for Axial Stresses, Shear Stresses, and Shear Center

Description: Report presenting a practical and relatively rapid method of compensating for shear lag in box-beam analysis with accuracy sufficient for design purposes. Effectiveness curves for box beam elements are derived for an ideal, symmetrical structure. Tabular computation forms for rapid, accurate calculations of axial stresses, shear center, and shear stresses for beam with shear lag are induced.
Date: April 1942
Creator: Erlandsen, Oscar, Jr. & Mead, Lawrence M., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Meteorological-Physical Limitations of Icing in the Atmosphere

Description: The icing hazard can, in most cases, be avoided by correct execution of the flights according to meteorological viewpoints and by meteorologically correct navigation (horizontal and, above all, vertical). The zones of icing hazard are usually narrowly confined. Their location can be ascertained with, in most cases, sufficient accuracy before take-off.
Date: January 1939
Creator: Findeisen, W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Effect of Advance Ratio on Flight Performance of a Modified Supersonic Propeller

Description: Note presenting results of a flight investigation to determine the aerodynamic characteristics of a supersonic propeller modified by the incorporation of higher than optimum advance angles. The propeller was designed for a forward Mach number of 0.95, an advance ratio of 3.2, and a power coefficient of 0.42. The efficiency of the propeller is approximately 79 percent at a Mach number of 0.95.
Date: September 1958
Creator: Hammack, Jerome B. & O'Bryan, Thomas C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On possible similarity solutions for three-dimensional incompressible laminar boundary layers 1: similarity with respect to stationary rectangular coordinates

Description: From Summary: "Solutions of mainstream flow patterns for all possible incompressible laminar-boundary-layer flows having classical similarity with respect to rectangular coordinate systems are derived. These solutions, which apply to a wide range of flows, are summarized in table form."
Date: October 1956
Creator: Hansen, Arthur G. & Herzig, Howard Z.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of behavior of simply supported flat plates compressed beyond the buckling load into the plastic range

Description: From Summary and Introduction: "An analysis is presented of the postbuckling behavior of a simply supported square flat plate with straight edges compressed beyond the buckling load into the plastic range. The method of analysis involves the application of a variational principle of the deformation theory of plasticity in conjunction with computations carried out on a high-speed calculating machine. The results of the analysis are presented in the form of curves showing the variation of deforma… more
Date: February 1955
Creator: Mayers, J. & Budiansky, Bernard
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A survey of unclassified axial-flow-compressor literature

Description: A survey of unclassified axial-flow-compressor literature is presented in the form of brief reviews of the methods, results, and conclusions of selected reports. The reports are organized into several main categories with subdivisions, and frequent references are made within the individual reviews to pertinent material elsewhere in the survey.
Date: November 8, 1955
Creator: Herzig, Howard Z. & Hansen, Arthur G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Presentation on Facility Problems in High-Temperature Structures Research

Description: "This presentation is intended to reflect the current general approach of the NACA to the problems of high-temperature structures research facilities. The facilities and problems discussed apply to flight in the Mach number range from 2 to about 20. It is emphasized that this field is one in which the thinking is rapidly changing and the facilities investigations discussed, particularly for the higher temperature range, are in the exploratory stage" (p. 1).
Date: March 27, 1956
Creator: Purser, Paul E. & Heldenfels, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

General tank tests on the hydrodynamic characteristics of four flying-boat hull models of differing length-beam ratio

Description: Report presenting the results of general tests on the hydrodynamic characteristics of four related flying-boat hull models of differing length-beam ratio. Five different characteristics were investigated in an effort to gain perspective and determine which characteristics were most important: resistance, porpoising, main forebody spray blister, bow spray in rough water, and yawing stability near hump speeds.
Date: June 1944
Creator: Davidson, Kenneth S. M.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Presentation on facility problems in high-temperature structures research

Description: Presentation regarding the current general approach of NACA to the problems of high-temperature structures research facilities. The field is rapidly changing and many investigations discussed are still in the exploratory stage. The main areas of importance are heating, loading, and structural model accommodation as well as having the proper research equipment and heat exchangers.
Date: March 27, 1956
Creator: Purser, Paul E. & Heldenfels, Richard R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Automatic Stabilization

Description: This report lays more stress on the principles underlying automatic piloting than on the means of applications. Mechanical details of servomotors and the mechanical release device necessary to assure instantaneous return of the controls to the pilot in case of malfunction are not included. Descriptions are provided of various commercial systems.
Date: December 1936
Creator: Haus
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic Characteristics of a 45 Degree Swept-Back Wing With Aspect Ratio of 3.5 and NACA 2S-50(05)-50(05) Airfoil Sections

Description: From Introduction: "The present paper presents the scale effect on the longitudinal aerodynamic characteristics, the aerodynamic characteristics in yaw, and the tuft studies for 0^o and 3.7^o yaw. The results of the effect of leading-edge and trailing-edge flaps on the aerodynamic characteristics of the wing will be presented in later reports."
Date: August 4, 1947
Creator: Proterra, Anthony J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Wing-body interference at supersonic speeds with an application to combinations with rectangular wings

Description: Report presenting the development of an exact theoretical method that permits the determination of the pressure field of a wing-body combination with a circular body and a wing with supersonic leading and trailing edges. Detailed calculations were performed for wing-body combinations composed of rectangular wings mounted at incidence on bodies at zero angle of attack for effective chord-radius ratios of 4 or less.
Date: April 1952
Creator: Nielsen, Jack N. & Pitts, William C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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