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Technical Report Archive and Image Library
902
National Advisory Committee for Aeronautics Collection
743
Texas Attorney General Opinions
468
Office of Scientific & Technical Information Technical Reports
114
TRAIL Microcard Collection
95
Texas State Publications
17
Government Documents A to Z Digitization Project
8
USGS Topographic Map Collection
7
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4
United States Experiment Station Record
3
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NACA Research Memorandums
323
NACA Technical Notes
302
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111
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79
NACA Technical Reports
37
United States Bureau of Mines Reports
21
MDDC (Series)
19
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14
Texas Game and Fish
12
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1,535 Matching Results
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Icing Properties of Noncyclonic Winter Stratus Clouds
Note presenting measurements of the vertical distribution of liquid water concentration and drop size in winter stratus clouds in the absence of significant cyclonic or frontal activity. The observations indicate that the clouds are formed by turbulent mixing of the lower layers of the atmosphere, resulting in a region of constant specific humidity and adiabatic lapse rates. Calculations based on the observations were used to construct a graph that gives the liquid water concentration in terms of the temperature at the cloud base and the height above the base.
Date:
September 1947
Creator:
Lewis, William
Object Type:
Report
System:
The UNT Digital Library
NACA Conference on Aerodynamic Problems of Transonic Airplane Design
Compilation of the papers presented at a NACA conference on transonic airplane design, including stability and control and configurations with extreme sweep. From Introduction: "The purpose of this conference was to convey to those involved in the study of the aerodynamic problems of transonic aircraft these recent research results and to provide those attending an opportunity for discussion of the results."
Date:
1947-11-05/1947-11-06
Creator:
unknown
Object Type:
Report
System:
The UNT Digital Library
Systematic Wind-Tunnel Measurements on a Laminar Wing With Nose Flap
"Results of measurements are given as a supplement to earlier tests for a laminar profile with nose flap; magnitude, form, and angle of attack of the flap were systematically changed. The experiments were carried out at an effective Reynolds number of 8.2 x 10(exp 5). A comparison with measurements on other profiles shows that the effect of a nose flap is essentially dependent upon magnitude of the nose radius coefficient of the profile" (p. 1).
Date:
April 1947
Creator:
Krueger, W.
Object Type:
Report
System:
The UNT Digital Library
Theoretical Investigation of Drag Reduction in Maintaining the Laminar Boundary Layer by Suction
"Maintenance of a laminar boundary layer by suction was suggested recently to decrease the friction drag of an immersed body, in particular an airfoil section. The present treatise makes a theoretical contribution to this question in which, for several cases of suction and blowing, the stability of the laminar velocity profile is investigated. Estimates of the minimum suction quantities for maintaining the laminar boundary layer and estimates of drag reduction are thereby obtained" (p. 1).
Date:
June 1947
Creator:
Ulrich, A.
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel investigation of the effect of tab balance on tab and control-surface characteristics
An investigation was conducted to furnish data on the effect of tab balance on tab and control-surface characteristics. The airfoil tested had a modified NACA 65(1)-012 contour with a plain flap having a chord equal to 25 percent of the wing chord and with a tab having a chord equal to 25 percent of the flap chord and having several nose shapes and overhang lengths. The results of the investigation indicated that, in general, tab balance affected tab hinge-moment characteristics in much the same manner that flap balance affects flap hinge-moment characteristics. A moderate amount of tab balance did not seem to have any adverse effect on flap hinge-moment characteristics.
Date:
August 1947
Creator:
Brewer, Jack D. & Queijo, M. J.
Object Type:
Report
System:
The UNT Digital Library
Effects of sweepback on boundary layer and separation
"Following the law of stress adopted in the Navier-Stokes equations, the configuration of the viscous flow in planes at right angles to the axis of an infinite cylinder is found to be independent of the axial motion of the cylinder. In the limiting case of a yawed or swept wing of very high aspect ratio, certain boundary-layer and separation phenomena are thus determined independently by the crosswise component of velocity" (p. 1).
Date:
July 1947
Creator:
Jones, Robert T.
Object Type:
Report
System:
The UNT Digital Library
Introduction to the Problem of Rocket-Powered Aircraft Performance
An introduction to the problem of determining the fundamental limitations on the performance possibilities of rocket-powered aircraft is presented. Previous material on the subject is reviewed and given in condensed form along with supplementary analyses. Some of the problems discussed are: 1) limiting velocity of a rocket projectile; 2) limiting velocity of a rocket jet; 3) jet efficiency; 4) nozzle characteristics; 5) maximum attainable altitudes; 6) ranges. Formulas are presented relating the performance of a rocket-powered aircraft to basic weight and nozzle dimensional parameters. The use of these formulas is illustrated by their application to the special case of a nonlifting rocket projectile.
Date:
December 1947
Creator:
Ivey, H. Reese; Bowen, Edward N., Jr. & Oborny, Lester F.
Object Type:
Report
System:
The UNT Digital Library
Elastic Properties in Tension and Shear of High Strength Nonferrous Metals and Stainless Steel - Effect of Previous Deformation and Heat Treatment
"A resume is given of an investigation of the influence of plastic deformation and of annealing temperature on the tensile and shear elastic properties of high strength nonferrous metals and stainless steels in the form of rods and tubes. The data were obtained from earlier technical reports and notes, and from unpublished work in this investigation. There are also included data obtained from published and unpublished work performed on an independent investigation" (p. 1).
Date:
March 1947
Creator:
Mebs, R. W. & McAdam, D. J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Tests of the Landing on Water of a Model of a High-Speed Airplane - Langley Tank Model 229
Memorandum presenting an investigation at the tank no. 2 monorail of the landing on smooth water of a scale model of a hypothetical jet- and rocket-propelled airplane designed to fly at transonic speeds. The test is part of an investigation of the feasibility of the operation from water of high-speed airplanes. The results of the test form a basis for evaluating the improvement in hydrodynamic characteristics.
Date:
December 9, 1947
Creator:
King, Douglas A.
Object Type:
Report
System:
The UNT Digital Library
A Method for Calculating the Heat Required for Windshield Thermal Ice Prevention Based on Extensive Flight Tests in Natural Icing Conditions
Report presenting an equation for calculating the heat flow required from the surface of an internally heated windshield in order to prevent ice accretions during flight in specified icing conditions. Results regarding the internally heated windshield characteristics, external discharge windshields, and prediction of heating requirements for both types of windshields are provided.
Date:
November 1947
Creator:
Jones, Alun R.; Holdaway, George H. & Steinmetz, Charles P.
Object Type:
Report
System:
The UNT Digital Library
Investigation of Effects of Surface Temperature and Single Roughness Elements on Boundary-Layer Transition
Note presenting an investigation of the laminar boundary layer and the position of the transition point on a heated flat plate. The Reynolds number of transition was found to decrease as the temperature of the plate is increased. Results regarding the effect of surface temperature, effect of roughness elements, mean-velocity profile near a heated wall, instability of inflection-point profiles, and laminar separation and transition are provided.
Date:
April 1947
Creator:
Liepmann, Hans W. & Fila, Gertrude H.
Object Type:
Report
System:
The UNT Digital Library
Investigation of the Aileron and tab of a spring-tab lateral-control system in the Langley 19-foot pressure tunnel
Report presenting tests of a partial-span model of a large bomber-type airplane, which were conducted to provide data on the aerodynamic characteristics of the aileron-tab arrangement and of the wing. Testing occurred to determine the rolling-moment, yawing-moment, and hinge-moment characteristics of the aileron and tab and the effect of midchord wing slots on the characteristics of the wing and aileron and tab. Results regarding the aerodynamic and stalling characteristics of the wing and aerodynamic characteristics of the aileron and tab are provided.
Date:
September 1947
Creator:
Deters, Owen J. & Russell, Robert T.
Object Type:
Report
System:
The UNT Digital Library
Notes and Tables for Use in the Analysis of Supersonic Flow
Paper presenting a compilation of formulas, tables, and curves that have been found to be useful in the analysis of supersonic wind-tunnel data.
Date:
December 1947
Creator:
The Staff of the Ames 1- by 3-foot Supersonic Wind-Tunnel Section
Object Type:
Report
System:
The UNT Digital Library
Flight Measurements of the Lateral Control Characteristics of Narrow-Chord Ailerons on the Trailing Edge of a Full-Span Slotted Flap
Note presenting results of flight tests made to determine the effect of flap deflection on the lateral control characteristics of a modified Brewster F2A-2 airplane equipped with partial-span narrow-chord ailerons on the trailing edge of a full-span NACA slotted flap. The results indicated that the effectiveness of the ailerons was greatly reduced at flap deflections greater than about 20 degrees.
Date:
February 1947
Creator:
Sawyer, Richard H.
Object Type:
Report
System:
The UNT Digital Library
Instantaneous ultraviolet knock spectra correlated with high-speed photographs
Report presenting an investigation to obtain a record of any chemical changes directly associated with knock in a spark-ignition engine on a greatly magnified time scale by means of coordinated high-speed motion pictures and spectrograms.
Date:
August 1947
Creator:
Hirshfeld, M. A. & Miller, Cearcy D.
Object Type:
Report
System:
The UNT Digital Library
Theoretical additional span loading characteristics of wings with arbitrary sweep, aspect ratio, and taper ratio
From Summary: "The Weissinger method for determining additional span loading has been used to find the lift-curve slope, spanwise center of pressure, aerodynamic center location, and span loading coefficients of untwisted and uncambered wings having a wide range of plan forms characterized by various combinations of sweep, aspect ratio, and taper ratio. The results are presented as variations of the aerodynamic characteristics with sweep angle for various values of aspect ratio and taper ratio. Methods are also included for determining induced drag and the approximate effects of compressibility."
Date:
December 1947
Creator:
DeYoung, John
Object Type:
Report
System:
The UNT Digital Library
A comparison of three theoretical methods of calculating span load distribution on swept wings
Report presenting the application of three methods for calculating span load distribution for five swept wings. The methods were examined to establish their relative accuracy and ease of application. While the Weissinger and Falkner methods were more useful for certain circumstances, there were no advantages noted with the Mutterperl method.
Date:
November 1947
Creator:
Van Dorn, Nicholas H. & DeYoung, John
Object Type:
Report
System:
The UNT Digital Library
Propeller-efficiency charts for light airplanes
Report presenting some charts on the reflection of a propeller on the basis of efficiency for application to a light airplane design. Various values of power are covered for several different airspeeds, propeller diameters, and blade numbers.
Date:
July 1947
Creator:
Crigler, John L. & Jaquis, Robert E.
Object Type:
Report
System:
The UNT Digital Library
Charts Showing Relations Among Primary Aerodynamic Variables for Helicopter-Performance Estimation
"In order to facilitate solutions of the general problem of helicopter selection, the aerodynamic performance of rotors is presented in the form of charts showing relations between primary design and performance variables. By the use of conventional helicopter theory, certain variables are plotted and other variables are considered fixed. Charts constructed in such a manner show typical results, trends, and limits of helicopter performance" (p. 1).
Date:
February 1947
Creator:
Talkin, Herbert W.
Object Type:
Report
System:
The UNT Digital Library
Effect of Finite Span on the Airload Distributions for Oscillating Wings 1: Aerodynamic Theory of Oscillating Wings of Finite Span
Note presenting a formula for the pressure distribution on an oscillating lifting surface of finite span under the assumption of a ratio of span to average chord that is not too small. It is found that the effect of three-dimensionality of the flow may be incorporated in the results of the two-dimensional theory by adding a correction factor to the basic function of the two-dimensional theory.
Date:
March 1947
Creator:
Reissner, Eric
Object Type:
Report
System:
The UNT Digital Library
Critical Stress of Thin-Walled Cylinders in Axial Compression
"Empirical design curves are presented for the critical stress of thin-walled cylinders loaded in axial compression. These curves are plotted in terms of nondimensional parameters of small-deflection theory and are compared with theoretical curves derived for the buckling of cylinders with simply supported and clamped edges. An empirical equation is given for the buckling of cylinders having a length-radius ratio greater than about 0.75" (p. 1).
Date:
June 1947
Creator:
Batdorf, S. B.; Shildcrout, Murry & Stein, Manuel
Object Type:
Report
System:
The UNT Digital Library
A Simplified Method for Elastic Stability Analysis for Thin Cylindrical Shells 2: Modified Equilibrium Equation
Note presenting a derivation of a modified form of Donnell's equation for the equilibrium of thin cylindrical shells which is equivalent to Donnell's equation but has certain advantages in physical interpretation and in ease of solution, particularly in the case of shells with clamped edges. The modified equation can be solved for the buckling stresses of curved sheet having either simply supported or clamped edges by established methods essentially equivalent to those in use for flat sheet.
Date:
June 1947
Creator:
Batdorf, S. B.
Object Type:
Report
System:
The UNT Digital Library
Effect of Exhaust Pressure on the Performance of an 18-Cylinder Air-Cooled Radial Engine with a Valve Overlap of 40 Degrees
Note presenting an investigation to determine the effect of exhaust pressure on the performance of an 18-cylinder air-cooled radial engine equipped with a conventional exhaust collector ring. The engine power increased at a diminishing rate as exhaust pressure decreased.
Date:
March 1947
Creator:
Boman, David S.; Nagey, Tibor F. & Doyle, Ronald B.
Object Type:
Report
System:
The UNT Digital Library
Effect of Product of Inertia on Lateral Stability
Note presenting a theoretical investigation made to determine the effect of the product-of-inertia terms in the lateral equations of motion on the lateral-stability boundaries. The product of inertia results from the inclination of the principal longitudinal axis of the airplane to the flight path. The results indicated that the product-of-inertia terms should be included in the lateral equations of motion to determine the lateral stability of an airplane.
Date:
March 1947
Creator:
Sternfield, Leonard
Object Type:
Report
System:
The UNT Digital Library