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Technical Report Archive and Image Library
472
National Advisory Committee for Aeronautics Collection
380
Texas Attorney General Opinions
191
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91
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61
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25
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24
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18
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824 Matching Results
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Classified list of United States government publications
The Classified List includes all classes of publications available for distribution to depository libraries. This list includes the selections made by the North Texas State College library beginning in April 1948.
Date:
June 1, 1947
Creator:
United States. Government Printing Office.
Object Type:
Book
System:
The UNT Digital Library
A Colorimetric Method
From abstract: "This paper gives a method for determining Uranium using sodium cresotate as a colorimetric reagent. A precision is obtained of better than 2%. In carrying out analyses for Uranium in corrosion products by existing methods such as ignition to the oxide, silver reductor, or titration with ceric sulfate, it became apparent that a rapid, fairly accurate method for determining uranyl ion would be of great value. Such a method is described in this paper. The most logical color to use is that given by the ferrocyanide complex, but upon studying this, it proved to be unsatisfactory. Sodium salycilate also gives a color which has been used with some success, but its color appears to fade and is not very sensitive. A similar compound, sodium cresotate, was found to give an orange-red color and is the reagent used in the method to be described."
Date:
June 30, 1943
Creator:
Priest, H. F. & Priest, G. I.
Object Type:
Report
System:
The UNT Digital Library
Column and plate compressive strengths of aircraft structural materials: 17S-T aluminum-alloy sheet
From Summary: "Column and plate compressive strengths of 17S-T aluminum-alloy sheet were determined both within and beyond the elastic range from tests of thin-strip columns and from local-instability tests of formed Z- and channel-section columns. These tests are part of an extensive research investigation to provide data on the structural strengths of various aircraft materials. Results are presented in the form of curves and charts that may be used in the design and analysis of aircraft structures."
Date:
June 1945
Creator:
Heimerl, George J. & Roy, J. Albert
Object Type:
Report
System:
The UNT Digital Library
Column and Plate Compressive Strengths of Aircraft Structural Materials: 24S-T Aluminum-Alloy Sheet
"Column and plate compressive strengths of 24S-T aluminum-alloy sheet were determined both within and beyond the elastic range from tests of thin-strip columns and from local-instability tests of formed Z-end channel-section columns. These tests are the first of a series in an extensive research investigation to provide data on the structural strength of various aircraft materials. The results, which are presented in the form of curves and charts that may be used in the design and analysis of aircraft structures, supersede preliminary results published previously" (p. 1).
Date:
June 1945
Creator:
Lundquist, Eugene E.; Schuette, Evan H.; Heimerl, George J. & Roy, J. Albert
Object Type:
Report
System:
The UNT Digital Library
Comparative Effectiveness of a Convection Type and a Radiation-Type Cooling Cap on a Turbosupercharger
Note presenting an investigation to compare the effectiveness of two basic methods of cooling a turbosupercharger and to obtain data on the temperature level and distribution in the turbine wheel. Turbine-wheel temperatures were obtained for various conditions of cooling-air mass flow, exhaust-gas temperature, and exhaust-gas mass flow. Modified forms of the standard cooling caps were used to allow for the installation of temperature-measuring devices.
Date:
June 1946
Creator:
Hartwig, Frederick J., Jr.
Object Type:
Report
System:
The UNT Digital Library
Comparative Results of Tests on Several Different Types of Nozzles
"This paper presents the results of tests conducted to determine the effect of the constructional elements of a Laval nozzle on the velocity and pressure distribution and the magnitude of the reaction force of the jet. The effect was studied of the shapes of the entrance section of the nozzle and three types of divergent sections: namely, straight cone, conoidal with cylindrical and piece and diffuser obtained computationally by a graphical method due to Professor F. I. Frankle. The effect of the divergence angle of the nozzle on the jet reaction was also investigated" (p. 1).
Date:
June 1944
Creator:
Kisenko, M. S.
Object Type:
Report
System:
The UNT Digital Library
Comparative Tests of High Voltage Resistors Used for Voltmeter Bleeders
The following report describes tests made for the purpose of determining the accuracy and permanency of various types of high resistance bleeders, and their resistance variation during use over a period of approximately six months.
Date:
June 19, 1944
Creator:
Grauer, Carl T.
Object Type:
Report
System:
The UNT Digital Library
Comparison of Hovering Performance of Helicopters Powered by Jet-Propulsion and Reciprocating Engines
Report presenting an investigation of the maximum hovering time, or the time that a helicopter can sustain itself without motion, for helicopters using a reciprocating engine, by ramjet engines at the tips of rotor blades, and by pulse-jet engines at the tips of rotor blades. Testing showed that the reciprocating engine permitted much longer hovering time than the jet-propulsion engines, but the jet-propulsion engines were much lighter and could lift greater disposable loads.
Date:
June 11, 1948
Creator:
Brightwell, Virginia L.; Peters, Max D. & Sanders, J. C.
Object Type:
Report
System:
The UNT Digital Library
Comparison of performance of AN-F-58 and AN-F-32 fuels in J33-A-23 turbojet engine
Report presenting an investigation using a 4600 pound-thrust turbojet engine as part of a program to determine the comparative performance of fuels conforming to specifications AN-F-58 and AN-F-32. Results regarding the altitude performance, altitude low-speed blow-out limits, idling limits of fuel-metering control, altitude windmilling starts, carbon-deposition rates, and iron oxide contamination are provided.
Date:
June 2, 1949
Creator:
Wilsted, H. D. & Armstrong, J. C.
Object Type:
Report
System:
The UNT Digital Library
A Comparison of the Effects of Four-Blade Dual- and Single-Rotation Propellers on the Stability and Control Characteristics of a High-Powered Single-Engine Airplane
Report presenting a scale powered model of the Douglas XSB2D-1 airplane tested with a four-blade dual-rotation propeller and a four-blade single-rotation propeller. To make the results more directly comparable, no other changes were made to the model. Results regarding longitudinal stability, directional characteristics, and lateral stability are provided.
Date:
June 1944
Creator:
Harper, Charles W. & Wick, Bradford H.
Object Type:
Report
System:
The UNT Digital Library
A comparison of three spinner-diffuser designs in an NACA D(sub S) cowling for the Pratt & Whitney R-2800 engine
Report presenting testing to determine which of three spinner-diffuser designs on an NACA cowling was the most effective in cooling a Pratt & Whitney R-2800 engine installation. The results of pressure-distribution studies in front of and behind each bank of cylinders are presented for a wide range of propeller-operating conditions.
Date:
June 1944
Creator:
Habel, Louis W. & Korycinski, Peter F.
Object Type:
Report
System:
The UNT Digital Library
A comparison of three theoretical methods of calculating span load distribution on swept wings
From Summary: "Three methods for calculating span load distribution, those developed by V.M Falkner, Wm. Mutterperl, and J. Weissinger, have been applied to five swept wings. The angles of sweep ranged from -45 degrees to +45 degrees. These methods were examined to establish their relative accuracy and case of application. Experimentally determined loadings were used as a basis for judging accuracy. For the convenience of the readers the computing forms and all information requisite to their application are included in appendixes. From the analysis it was found that the Weissinger method would be best suited to an over-all study of the effects of plan form on the span loading and associated characteristics of wings."
Date:
June 9, 1947
Creator:
Van Dorn, Nicholas H. & DeYoung, John
Object Type:
Report
System:
The UNT Digital Library
Completed Tabulation in the United States of Tests of 24 Airfoils at High Mach Numbers (Derived From Interrupted Work at Guidonia, Italy in the 1.31- by 1.74-Foot High-Speed Tunnel)
Two-dimensional data were obtained in Mach range of from 0.40 to 0.94 and Reynolds Number range of (3.4 - 4.2) X 10 Degrees. Results indicate that thickness ratio is dominating shape parameter at high Mach numbers and that aerodynamic advantages are attainable by using thinnest possible sections. Effects of jet boundaries, Reynolds Number, and Data presented are free from jet-boundary and humidity effects.
Date:
June 1945
Creator:
Ferri, Antonio
Object Type:
Report
System:
The UNT Digital Library
Composition and Thermal Decomposition of Uranyl Peroxide
Technical report on the studies that have been made on the composition and thermal decomposition of uranyl peroxide. The conditions of precipitation and drying have been found to have no appreciable effect on the composition of the compound, but do affect the physical appearance of the precipitate and the rate of thermal decomposition. The UO4 + 2H2O appears to be thermodynamically unstable with respect to UO3 at 25 degrees C and atmospheric pressure, although the rate of conversion is extremely slow. The UO4 + 2H2O is completely converted to UO3 on standing at 150 degrees C and atmospheric pressure for two weeks. Partially decomposed uranyl peroxide samples contain extra oxygen which is released on immersing the sample in water.
Date:
June 30, 1945
Creator:
Leininger, R. F.; Hunt, J. P. & Koshland, D. E., Jr.
Object Type:
Report
System:
The UNT Digital Library
Compression Shocks of Detached Flow
"It is known that compression shocks which lead from supersonic to subsonic velocity cause the flow to separate on impact on a rigid wall. Such shocks appear at bodies with circular symmetry or wing profiles on locally exceeding sonic velocity, and in Laval nozzles with too high a back pressure. The form of the compression shocks observed therein is investigated" (p. 1).
Date:
June 1947
Creator:
Eggink
Object Type:
Report
System:
The UNT Digital Library
Compressive Strength of Flat Panels with Z- and Hat-Section Stiffeners
Compression tests were conducted on 247 panels with Z-section stiffeners and 304 panels with hat-section stiffeners. Specimens were constructed from artificially aged Alclad 24S aluminum alloy with minimum guaranteed yield strengths of 64 and 57 ksi for stiffeners and sheet materials, respectively. Height, thickness, and spacing of stiffeners, sheet thickness, and length of specimens were varied systematically to show effects of changes in these dimensions on panel strength. Results show average stresses at buckling load and maximum load.
Date:
June 1944
Creator:
Kotanchik, Joseph N.; Weinberger, Robert A.; Zender, George W. & Neff, John, Jr.
Object Type:
Report
System:
The UNT Digital Library
Computation of Thin-Walled Prismatic Shells
"We consider a prismatic shell consisting of a finite number of narrow rectangular plates and having in the cross-section a finite number of closed contours (fig. 1(a)). We shall assume that the rectangular plates composing the shell are rigidly joined so that there is no motion of any kind of one plate relative to the others meeting at a given connecting line. The position of a point on the middle prismatic surface is considered to be defined by the coordinate z, the distance to a certain initial cross-section z = O, end the coordinate s determining its position on the contour of the cross-section" (p. 1).
Date:
June 1949
Creator:
Vlasov, V. Z.
Object Type:
Report
System:
The UNT Digital Library
Consideration of Dynamic Loads on the Vertical Tail by the Theory of Flat Yawing Maneuvers
"Dynamic yawing effects on vertical tail loads are considered by a theory of flat yawing maneuvers. A comparison is shown between computed loads and the loads measured in flight in a fighter airplane. The dynamic effects were investigated on a large flying boat for both an abrupt rudder deflection and a sinusoidal rudder deflection" (p. 1).
Date:
June 1946
Creator:
Boshar, John & Davis, Philip
Object Type:
Report
System:
The UNT Digital Library
The Contamination of Cooling Water by a P-9 Plant
The following sources of contamination in cooling water of the P-9 plant are considered: (1) Fission recoils, (2) Corrosion of metal, (3) Recoil from aluminum, (4) Induced activity in the water. It is found that for a P-9 plant of 3.5 x 10(4) KW contamination of the river at "X" should not exceed the .1 r criterion unless coating failure occurs. Tables of the amount of coating failure permissible are given as a function of holdup time.
Date:
June 1, 1943
Creator:
Friedman, Francis L. (Francis Lee), 1918-
Object Type:
Report
System:
The UNT Digital Library
Contribution to the Problem of Flow at High Speed
Report divided into two sections about flow problems encountered at high speeds. The topics include: 1) A Few General Remarks Covering the Prandtl-Busemann Method; and 2) Effect of Compressibility in Axially Symmetrical Flow around an Ellipsoid.
Date:
June 1949
Creator:
Schmieden, C. & Kawalki, K. H.
Object Type:
Report
System:
The UNT Digital Library
Control during starting of gas-turbine engines
Report presenting an investigation of the variables pertinent to the control of gas temperatures of gas-turbine engines during starting conducted by obtaining time records of the variables involved during actual starting conditions. Poor control of gas temperatures during starting was found to be caused by an accumulation of fuel in the engine before ignition and excessive fuel-flow rates at the time of ignition.
Date:
June 17, 1948
Creator:
Koenig, Robert J. & Dandois, Marcel
Object Type:
Report
System:
The UNT Digital Library
Cooling Characteristics of a Pratt and Whitney R-2800 Engine Installed in an NACA Short-Nose High-Inlet-Velocity Cowling
An investigation was made of the cooling characteristics of a P and W R-2800 engine with NACA short-nose high inlet-velocity cowling. The internal aerodynamics of the cowling were studied for ranges of propeller-advance ratio and inlet-velocity ratio obtained by deflection of cowling flaps. Tests included variations of engine power, fuel/air ratio and cooling-air pressure drop. Engine cooling data are presented in the form of cooling correlation curves, and an example for calculation of cooling requirements in flight is included.
Date:
June 1944
Creator:
Corson, Blake W. & McLellan, Charles H.
Object Type:
Report
System:
The UNT Digital Library
Cooling Effects of an Airplane Equipped With an NACA Cowling and a Wing-Duct Cooling System
Report presenting cooling tests of a Northrop A-17A attack airplane equipped with a conventional NACA cowling and then with a wing-duct cooling system. Ground cooling for the wing-duct system without cowl flap was better than for the cowling with flap, but was improved by installing a cowl flap. Satisfactory temperatures were maintained in climb and high-speed flight, but a greater quantity of cooling air was needed for the wing-duct system.
Date:
June 1941
Creator:
Turner, L. I., Jr.; Bierman, David & Boothby, W. B.
Object Type:
Report
System:
The UNT Digital Library
Cooling in Cruising Flight With Low Fuel-Air Ratios
Report presenting testing of a Pratt & Whitney R-1830-43 engine mounted in a B-24D nacelle in the full-scale wind tunnel in order to investigation the potential improvements of fuel economy. Suggestions for improving the cruising power and cruising range by operating at specified fuel-air ratios are provided.
Date:
June 1942
Creator:
Silverstein, Abe & Wilson, Herbert A., Jr.
Object Type:
Report
System:
The UNT Digital Library