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General method for computation of equilibrium composition and temperature of chemical reactions
Report presenting an approximation process that can be used to determine both composition and temperature resulting from a chemical reaction. It is suitable for use with any set of reactants over the complete range of mixture ratios as long as the products of reaction are ideal gases.
Date:
June 1950
Creator:
Huff, Vearl N. & Morrell, Virginia E.
System:
The UNT Digital Library
Study of effects of sweep on the flutter of cantilever wings
Report presenting an experimental and analytical investigation of the flutter of sweptback cantilever wings. The experiment employed groups of wings swept back by rotating and by shearing, with a range of angles of sweep tested. Comparison with experimental results indicated that the analysis is generally satisfactory for the main effects of sweep.
Date:
June 1950
Creator:
Barmby, J. G.; Cunningham, H. J. & Garrick, I. E.
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
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.
System:
The UNT Digital Library
Effects of fuel-nozzle carbon deposition on combustion efficiency of single tubular-type, reverse-flow turbojet combustor at simulated altitude conditions
Report presenting an investigation to study the effects of changes in fuel-nozzle carbon deposition on the combustion efficiency of a single tubular-type, reverse-flow, turbojet combustor. The investigation was conducted because of the need to improve the reproducibility of combustion data for fuel-research purposes.
Date:
June 1948
Creator:
Dittrich, Ralph T.
System:
The UNT Digital Library
Hydrodynamic impact loads in smooth water for a prismatic float having an angle of dead rise of 30 degrees
Report presenting an investigation involving a prismatic-float forebody of 30 degrees angle of dead rise subjected to impacts in smooth water as part of a series of impact tests to investigate the effects of angle of dead rise on hydrodynamic loads of floats and hulls. Results indicated that the loads encountered during impacts can be predicted within the limits of experimental accuracy by curves and equations.
Date:
June 1947
Creator:
Miller, Robert W. & Leshnover, Samuel
System:
The UNT Digital Library
Effect of Longitudinal Stiffeners on the Buckling Load of Long Flat Plates Under Shear
"An investigation was made to determine the effect of longitudinal stiffeners on the buckling load of long flat plates under shear. Tests were made of long flat plates reinforced by one and by two longitudinal stiffeners. A theoretical study of the buckling load of such plates, made by the energy method, is presented in the appendix. The results of the tests and the results of the theory are compared and are found to be in fair agreement" (p. 1).
Date:
June 1948
Creator:
Crate, Harold & Lo, Hsu
System:
The UNT Digital Library
Aerodynamic Characteristics of a Number of Modified NACA Four-Digit-Series Airfoil Sections
Report presenting theoretical pressure distributions and experimental aerodynamic characteristics at low speeds for a group of NACA four-digit series airfoil sections. Results regarding lift, drag, and pitching moment are provided.
Date:
June 1948
Creator:
Loftin, Laurence K., Jr. & Cohen, Kenneth S.
System:
The UNT Digital Library
An Investigation of a Thermal Ice-Prevention System for a Cargo Airplane 9: The Temperature of the Wing Leading-Edge Structure as Established in Flight
Report presenting flight measurements of structure temperatures occurring in the wing outer panel of the airplane in order to improve the design of thermal ice-prevention systems. Results indicate that structure temperatures increased almost in direct proportion with an increase in heated-air temperature.
Date:
June 1948
Creator:
Schlaff, Bernard A. & Selna, James
System:
The UNT Digital Library
Calculated performance of 12-cylinder liquid-cooled engine with exhaust-gas turbine geared to crankshaft
Report presenting computations of the horsepower and specific fuel consumption of a compound engine composed of an exhaust-gas turbine and an auxiliary supercharger geared to the crankshaft of a 12-cylinder liquid-cooled engine. Results regarding the engine exhaust pressure, engine speed, fuel-air ratio, inlet-manifold pressure, turbine, auxiliary-supercharger, and drive-gear efficiency, effect of altitude, comparison of compound and turbosupercharged engines, performance at high-power levels, effect of afterburning, and characteristics of a modified system are provided.
Date:
June 1948
Creator:
Desmon, Leland G. & Doyle, Ronald B.
System:
The UNT Digital Library
Application of Statistical Methods to Study of Gas-Turbine Blade Failures
Note presenting an investigation conducted to determine the applicability of statistical methods as an approach to the evaluation of materials for use in gas turbines by determining the frequency distribution of time until failure of gas-turbine blades. Two wheels, each incorporating 142 inserted blades of a cast cobalt-base heat-resistant alloy, were tested. The results indicated that the time for first failure may not generally be taken as an accurate indication of the performance of the average blade.
Date:
June 1948
Creator:
Hoffman, Charles A. & Ault, G. Mervin
System:
The UNT Digital Library
Standard Symbols for Helicopters
"A list of standard symbols for rotating-wing aircraft is presented. The list of symbols is subdivided for ready reference under appropriate headings, the symbols being restricted to those most generally used in studies of helicopter aerodynamics" (p. 1).
Date:
June 1948
Creator:
Gessow, Alfred
System:
The UNT Digital Library
Cylinder-Head Temperatures and Coolant Heat Rejections of a Multicylinder, Liquid-Cooled Engine of 1710-Cubic-Inch Displacement
Note presenting an extensive investigation of the cooling characteristics of a multicylinder, liquid-cooled aircraft engine of 1710-cubic-inch displacement. The results of the investigation are presented showing the variation of the cylinder-head temperature and the coolant heat rejection with the pertinent engine and coolant variables. Results regarding the relations between cylinder temperatures, effect of engine variables on average cylinder-head temperature between exhaust valves, coolant-flow distribution, effect of engine variables on heat rejection to coolant, and effect of coolant variables on coolant heat rejection are provided.
Date:
June 1948
Creator:
Povolny, John H. & Chelko, Louis J.
System:
The UNT Digital Library
Effect of size and number of outlet pipes on design of collectors for rating and testing axial-flow compressors
Report presenting an experimental investigation to determine the effect of design factors on the performance of collectors for axial-flow compressors, which consisted of airflow studies of an experimental collector on which six different outlet configurations were used. The size and number of outlet pipes had little effect on the static-pressure distribution at the collector inlet.
Date:
June 1948
Creator:
Moses, Jason J. & Kazberovich, Thomas I.
System:
The UNT Digital Library
Quantitative analysis of ternary mixtures of naphthalene, 1-methylnaphthalene, and 2-methylnaphthalene by ultraviolet spectrophotometry
Report presenting a method for quantitative analysis of ternary mixtures of naphthalene, 1-methylnaphthalene, and 2-methylnaphthalene on the basis of ultraviolet absorption in the region from 3000 to 3300 A and the effect of interference by a fourth absorber. Twelve synthetic ternary mixtures of three naphthalenes were analyzed with an average error of 0.8 percent of the alkylnaphthalenes present.
Date:
June 1948
Creator:
Cleaves, Alden P.; Carver, Mildred S. & Hibbard, Robert R.
System:
The UNT Digital Library
Effect of Hydrocarbon Type and Chain Length on Uniform Flame Movement in Quiescent Fuel-Air Mixtures
Report presenting the results of flame-speed measurements of quiescent fuel-air mixtures in a 2.5-centimeter horizontal glass tube of 16 straight-chain hydrocarbons of paraffin, olefin, diolefine, and acetylene series and four cyclic hydrocarbons presented in graphical form. Results regarding peak flame velocity and uniform flame velocity are provided.
Date:
June 1948
Creator:
Reynolds, Thaine W. & Ebersole, Earl R.
System:
The UNT Digital Library
A method for determination of aromatics in 150 degree to 300 degree C fractions of crude petroleum by measurement of aniline-point rise
Report presenting a method for determining aromatics in several fractions of crude petroleum. A general curve for analysis of cuts of crude petroleum with molal average boiling points near 218 degrees Celsius is presented.
Date:
June 1948
Creator:
Busch, Arthur M.; Cleaves, Alden P. & Hibbard, Robert R.
System:
The UNT Digital Library
Effect of landing flaps and landing gear on the spin and recovery characteristics of airplanes
Report presenting the effect of landing flaps and landing gear on the spin and recovery characteristics of airplanes as determined from investigations of the spinning characteristics of 58 models in the 15-foot and 20-foot free-spinning tunnels. Lowering flaps was generally found to cause an increase in inward sideslip, an increase in the angle of attack, and a decrease in the rate of rotation of the model in the spin.
Date:
June 1948
Creator:
Gale, Lawrence J.
System:
The UNT Digital Library
A Statistical Analysis of Gust-Velocity Measurements as Affected by Pilots and Airplanes
Note presenting gust data obtained during the U.S. Weather Bureau thunderstorm project in Orlando, Florida in 1946, which is analyzed statistically to determine the effects on the gust measurements of the several pilots and the several airplanes of the same model. The results indicate that, for three of the pilots and two of the airplanes, the effects on the gust measurements may introduce average errors of about 10 percent.
Date:
June 1948
Creator:
Press, Harry
System:
The UNT Digital Library
Low-speed wind-tunnel investigation of various plain-spoiler configurations for lateral control on a 42 degree sweptback wing
Report presenting a low-speed wind tunnel investigation of an exploratory nature in order to determine a satisfactory location for a spoiler lateral-control device for a sweptback wing. The semispan wing used for the tests had 42 degrees sweepback referred to the wing leading edge and an aspect ratio of 4.01. The best location appeared to be near the trailing edge of the wing, slightly inboard from the wing tip, and skewed with reference to the wing so as to be perpendicular to the free-stream air flow.
Date:
June 1948
Creator:
Schneiter, Leslie E. & Watson, James M.
System:
The UNT Digital Library
Chordwise and Spanwise Loadings Measured at Low Speed on a Triangular Wing Having an Aspect Ratio of Two and an NACA 0012 Airfoil Section
Note presenting pressure measurements on a triangular wing with an aspect ratio of 2 and an NACA 0012 airfoil section parallel to the center line. The wing angle of attack was varied from 4.3 to 48.1 degrees with the airspeed held constant at approximately 100 miles per hour. Results regarding chordwise pressure distribution, section lift characteristics, span load distribution, centers of pressure, and comparison of pressure data with force-test data are provided.
Date:
June 1948
Creator:
Wick, Bradford H.
System:
The UNT Digital Library
Supersonic Nozzle Design
"The theory of supersonic flow in nozzles is discussed, emphasis being placed on the physical rather than the mathematical point of view. Methods, both graphic and analytic, for designed nozzles are described together with a discussion of design factors. In addition, the analysis of given nozzle shapes to determine velocity distribution and possible existence of shock waves is considered" (p. 1).
Date:
June 1948
Creator:
Crown, J. Conrad
System:
The UNT Digital Library
Effects of nacelle position on wing-nacelle interference
Report presenting an investigation of the interference effects between an airfoil of high critical speed with no sweepback and a nacelle of high critical speed mounted in various positions with respect to the wing. The main objective was to obtain a wing-nacelle combination which has the force break occurring at a Mach number as high as for the wing alone. Results regarding the wings alone, pressure contours on wing and nacelle, influence of wing on nacelle, influence of nacelle on wing, and leading-edge modifications are provided.
Date:
June 1948
Creator:
McLellan, Charles H. & Cangelosi, John I.
System:
The UNT Digital Library
Experimental investigation of the effects of concentrated weights on flutter characteristics of a straight cantilever wing
Report presenting results to show the effects on the flutter characteristics of mounting concentrated weights at various positions on an untapered wing model. The moment of inertia, chordwise position of the weight, and spanwise position of the weight were varied. Results regarding the flutter parameters, flutter-speed ratio, flutter-velocity coefficients, and curves of ratio of first-bending frequency to torsion frequency and second-bending frequency to torsion frequency and provided.
Date:
June 1948
Creator:
Runyan, Harry L. & Sewall, John L.
System:
The UNT Digital Library