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Technical Report Archive and Image Library
98
National Advisory Committee for Aeronautics Collection
54
Office of Scientific & Technical Information Technical Reports
31
TRAIL Microcard Collection
22
Texas Attorney General Opinions
5
Government Documents A to Z Digitization Project
3
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1
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1
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NACA Research Memorandums
34
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21
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11
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10
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7
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6
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4
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4
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3
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3
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138 Matching Results
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Border Irrigation.
Provides instructions for implementing a border irrigation system for watering crops.
Date:
May 1951
Creator:
Core, Edwin J.
Object Type:
Book
System:
The UNT Digital Library
Grass Seed Production on Irrigated Land.
Provides recommendations for producing grass seed as a cash crop, using conservation-farming methods.
Date:
May 1951
Creator:
Omar, Harry F. & Stark, Russell Hunter
Object Type:
Book
System:
The UNT Digital Library
Preparing peaches for market.
Describes methods for harvesting, packing, and shipping peaches to be sold at market.
Date:
May 1951
Creator:
Morrison, W. W. (Wendell Wallace), 1897-
Object Type:
Book
System:
The UNT Digital Library
NACA Investigations of Icing-Protection Systems for Turbojet-Engine Installations
"Investigations have been made in flight and in wind tunnels to determine which components of turbojet installations are most critical in icing conditions, and to evaluate several methods of icing protection. From these studies, the requirements necessary for adequate icing protection and the consequent penalties on engine performance can be estimated. Because investigations have indicated that the compressor-inlet screen constitutes the greatest icing hazard and is difficult to protect, complete removal or retraction of the screen upon encountering an icing condition is recommended" (p. 1).
Date:
May 2, 1951
Creator:
von Glahn, Uwe; Callaghan, Edmund E. & Gray, Vernon H.
Object Type:
Report
System:
The UNT Digital Library
General plastic behavior and approximate solutions of rotating disk in strain-hardening range
Report presenting a partly linearized solution of plastic deformation of a rotating disk based on the deformation theory of plasticity and considering finite strains. The method can be used to investigate the general plastic behavior of a rotating disk.
Date:
May 1951
Creator:
Wu, M. H. Lee
Object Type:
Report
System:
The UNT Digital Library
Possible Application of Blade Boundary-Layer Control to Improvement of Design and Off-Design Performance of Axial-Flow Turbomachines
"A theoretical discussion of the application of blade boundary-layer control to increase the efficiency and the stage pressure ratio and to improve off-design performance of turbomachines is presented. A method based on the potential flow of a compressible fluid is developed for designing suction, or ejection, slotted blades having a prescribed velocity distribution along the blade and in the slot. The effect of the boundary layer on the design of the slot and the effect of ejecting gas at stagnation pressures and temperatures different from free-stream values are discussed" (p. 1).
Date:
May 1951
Creator:
Sinnette, John T., Jr. & Costello, George R.
Object Type:
Report
System:
The UNT Digital Library
Charts and tables for use in calculations of downwash of wings of arbitrary plan form
From Summary: "Values of the downwash of a horseshoe vortex in compressible flow are presented in the form of charts and tables. The use of the charts and tables in the calculations of the downwash of wings of arbitrary plan form is discussed. The results of a few calculations are compared with experimental results."
Date:
May 1951
Creator:
Diederich, Franklin W.
Object Type:
Report
System:
The UNT Digital Library
Floating characteristics of a plain and a horn-balanced rudder at spinning attitudes as determined from rotary tests on a model of a typical low-wing personal-owner airplane
Report presenting an investigation to determine the floating characteristics of full-length plain and horn-balanced rudders during rotary tests at spinning attitudes on a scale model of a typical low-wing personal-owner airplane. The investigation included the determination of the effects of the horizontal tail and the wing on the rudder floating characteristics.
Date:
May 1951
Creator:
Bihrle, William, Jr.
Object Type:
Report
System:
The UNT Digital Library
Turbulence-Intensity Measurements in a Jet of Air Issuing From a Long Tube
Report presenting data for turbulent-velocity-fluctuation components and mean-velocity distributions measured in the subsonic jet issuing from a pipe in which a fully developed turbulent flow was established. Axial and radial components of the fluctuation velocities were examined as functions of Reynolds number and position in the jet.
Date:
May 1951
Creator:
Little, Barney H., Jr. & Wilbur, Stafford W.
Object Type:
Report
System:
The UNT Digital Library
Torsional Strength of Stiffened D-Tubes
"The present report covers a series of torsional tests on stiffened D-tubes of alclad 24S-T3 aluminum alloy having a cross section similar to the NACA 0012 airfoil section and a closing web at 30 percent of the chord. The stiffeners consisted of ribs and stringers. An average-strength chart has been developed for this type of structure that takes into account the skin thickness, rib spacing, and stringer spacing. This chart may also be used for unstiffened D-tubes" (p. 1).
Date:
May 1951
Creator:
Kavanaugh, E. S. & Drinkwater, W. D.
Object Type:
Report
System:
The UNT Digital Library
On the Application of Mathieu Functions in the Theory of Subsonic Compressible Flow Past Oscillating Airfoils
Note presenting an account of explicit solutions in terms of Mathieu functions of the problem of two-dimensional subsonic compressible flow past oscillating airfoils. The results are applied to the calculation of three-dimensional corrections for the two-dimensional theory and the effect of the incorporation of the three-dimensional effects on the Mathieu function solution of the two-dimensional problem is shown.
Date:
May 1951
Creator:
Reissner, Eric
Object Type:
Report
System:
The UNT Digital Library
On Two-Dimensional Flow After a Curved Stationary Shock (With Special Reference to the Problem of Detached Shock Waves)
Note presenting an analysis of the problem of two-dimensional flow behind a curved stationary shock wave. The method assumes a given shock-wave shape, which automatically determines certain initial conditions on flow variables, and flow-pattern, including any body shape, follows from initial conditions.
Date:
May 1951
Creator:
Shu, S. S.
Object Type:
Report
System:
The UNT Digital Library
Analytical Evaluation of Aerodynamic Characteristics of Turbines With Nontwisted Rotor Blades
From Introduction: "The purpose the present report is to investigate the aerodynamic characteristics of nontwisted-rotor-blade turbines and to evaluate the characteristics of this type of design by comparison with the characteristics of free-vortex designs."
Date:
May 1951
Creator:
Slivka, William R. & Silvern, David H.
Object Type:
Report
System:
The UNT Digital Library
Friction at high sliding velocities of oxide films on steel surfaces boundary-lubricated with stearic-acid solutions
Report presenting experiments conducted to establish the capabilities of a fatty acid as an additive for lubrication of steel surfaces at high sliding velocities with severe loading and to determine the efficiency of prepared oxide films in this type of lubrication. Results regarding the lubrication with various concentrations, effect of surface oxides, load effects, and lubrication mechanism are provided.
Date:
May 1951
Creator:
Johnson, Robert L.; Peterson, Marshall B. & Swikert, Max A.
Object Type:
Report
System:
The UNT Digital Library
Analysis of experimental sea-level transient data and analog method of obtaining altitude response for turbine-propeller engine with relay-type speed control
From Introduction: "This report shows correlation between actual transient data obtained from the engine and solutions to a simulated system set up on an analog computer. Data are presented for response of engine speed to changes in set speed when the power plant was being controlled by a relay-type electronic governor that acted to maintain set speed by varying propeller pitch. Correlation obtained for sea-level conditions between actual time data and analog solutions is discussed."
Date:
May 17, 1951
Creator:
Vasu, George & Pack, George J.
Object Type:
Report
System:
The UNT Digital Library
Aerodynamic Characteristics of Wings Designed for Structural Improvement
From Wing Thickness: "A brief review of the effect of wing thickness and thickness distribution on the high-speed performance and stability characteristics of a representative configuration is presented."
Date:
May 28, 1951
Creator:
Weil, Joseph & Polhamus, Edward C.
Object Type:
Report
System:
The UNT Digital Library
Theoretical and Experimental Investigation of Additive Drag
"The significance of additive drag is discussed and equations for determining its approximate value are derived. Charts are presented giving values of additive drag for open-nose inlets and for annular-nose inlets with conical flow at the inlet. The effects of variable inlet total-pressure recovery and static pressures on the center body are investigated, and an analytical method of predicting the variation of pressure on the center body with mass-flow ratio is given" (p. 1).
Date:
May 21, 1951
Creator:
Sibulkin, Merwin
Object Type:
Report
System:
The UNT Digital Library
A comparison of the experimental and theoretical loading over triangular wings in sideslip at supersonic speeds
The results of an experimental investigation of the load distribution over two triangular wings in sideslip at Mach numbers from 1.20 to 1.79 are presented and compared with theory. The two wings tested have identical plan form, 45 degrees sweepback of the leading edge, and an aspect ratio of 4.0. One model was composed of round-nose airfoil sections and the other of sharp-nose, biconvex sections. For both wings the maximum thickness of streamwise sections was 6 percent and was located at the 30-percent chord.
Date:
May 18, 1951
Creator:
Boyd, John W.
Object Type:
Report
System:
The UNT Digital Library
Investigation of annular liquid flow with concurrent air flow in horizontal tubes
Report presenting visual observations and flow analyses made of annular liquid flow with cocurrent air flow in 2- and 4-inch-diameter horizontal transparent tubes. The experiments occurred over a range of air mass velocities, air temperatures, and Reynolds numbers. Results regarding the velocity and thickness of liquid films, description of water-film disturbances, effect of flow variables on liquid-film characteristics, and relation between disturbances and flow conditions are provided.
Date:
May 25, 1951
Creator:
Kinney, George R. & Abramson, Andrew E.
Object Type:
Report
System:
The UNT Digital Library
A semi-empirical method for calculating the pitching moment of bodies of revolution at low Mach numbers
A semiempirical method, in which potential theory is arbitrarily combined with an approximate viscous theory, for calculating the aerodynamic pitching moments for bodies of revolution is presented. The method can also be used for calculating the lift and drag forces. The calculated and experimental force and moment characteristics of 15 bodies of revolution are compared.
Date:
May 17, 1951
Creator:
Hopkins, Edward J.
Object Type:
Report
System:
The UNT Digital Library
Notes on Heat-Resistant Materials in Britain from Technical Mission October 13 to November 30, 1950
Memorandum presenting a summary of heat-resistant materials obtained from interviews with alloy producers, jet-engine manufacturers, and research laboratories in Britain during October and November 1950. The primary subjects of interest included the properties of materials and service requirements for gas turbines, criteria used for judging and inspecting materials, and research developments of both a practical and fundamental nature in the field.
Date:
May 14, 1951
Creator:
Freeman, J. W. & Cross, Howard C.
Object Type:
Report
System:
The UNT Digital Library
Wind-tunnel investigation at Mach numbers of 1.5 and 2.0 of a canard missile configuration
Report presenting wind-tunnel testing at Mach numbers of 1.5 and 2.0 to investigate the force, moment, and control characteristics of a canard missile configuration and its components in pitch and sideslip. The missile had small all-movable horizontal control surfaces at the nose and a cruciform wing at the rear, all of trapezoidal plan form. Trailing-edge flaps on the vertical fins were provided to supply directional control.
Date:
May 11, 1951
Creator:
Spahr, J. Richard & Robinson, Robert A.
Object Type:
Report
System:
The UNT Digital Library
Influence of airfoil trailing-edge angle and trailing-edge-thickness variation on the effectiveness of a plain flap at high subsonic Mach numbers
Report presenting the effects of variation of trailing-edge angle and trailing-edge thickness on the lift characteristics of a 10-percent-chord thick symmetrical NACA airfoil section with a 25-percent-chord plain flap as determined from wind tunnel tests over a range of Mach numbers. Results regarding the section lift and pitching-moment characteristics, variation of lift coefficient with flap deflection, schileren photographs, and effect of angle of attack are provided.
Date:
May 22, 1951
Creator:
Hemenover, Albert D. & Graham, Donald J.
Object Type:
Report
System:
The UNT Digital Library
Internal Flow and Burning Characteristics of 16-inch Ram Jet Operating in a Free Jet at Mach Numbers of 1.35 and 1.73
The effects of mass-flow ratio on the additive drag and normal-shock position of a single oblique-shock diffuser are presented. Also evaluated is the variation with operating condition of the velocity distribution at the combustion-chamber inlet. A comparison with connected-pipe data is included.
Date:
May 21, 1951
Creator:
Perchonok, Eugene & Farley, John M.
Object Type:
Report
System:
The UNT Digital Library