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339 Matching Results
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Column Strength of H-Sections and Square Tubes in Postbuckling Range of Component Plates
Note presenting a calculation of the column buckling stress in the range where the component plates have buckled using the method of split rigidities. Tests were carried out for a considerable range of slenderness ratios on three H-sections and two square tube sections.
Date:
August 1953
Creator:
Bijlaard, P. P. & Fisher, G. P.
System:
The UNT Digital Library
Comparison of flight and wind-tunnel measurements of high-speed-airplane stability and control characteristics
Report presenting a comparison of wind-tunnel and flight-measured values of stability and control characteristics. Generally, wind tunnels were found to predict all trends of characteristics reasonably well, but there are differences in parameters for certain values.
Date:
August 1956
Creator:
Williams, Walter C.; Drake, Hubert M. & Fischel, Jack
System:
The UNT Digital Library
A comparison of flight test results on a scout-bomber airplane with 4.7 degree and with 10 degree geometric dihedral in the wing outer panels
Report presenting a flight investigation of a scout-bomber airplane with 4.7 degrees and 10 degree geometric dihedral in the wing outer panels in order to obtain flight test results pertaining to the upper limit of the wing-dihedral angle for satisfactory handling qualities. No unusual or undesirable lateral control characteristics were observed with the combinations of stability parameters obtained with the two dihedral angles used.
Date:
August 1947
Creator:
Forsyth, Charles M. & Gray, William E., Jr.
System:
The UNT Digital Library
Comparison of relative sensitivities of the knock limits of two fuels to six engine variables
Report presenting knock testing of a sensitive fuel and a relatively insensitive fuel in a full-scale air-cooled cylinder. Six engine variables were investigated: fuel-air ratio, compression ratio, inlet-air temperature, spark advance, exhaust pressure, and cylinder temperature.
Date:
August 1946
Creator:
Cook, Harvey A.; Held, Louis F. & Pritchard, Ernest I.
System:
The UNT Digital Library
Comparison of stress-strain curves obtained by single-thickness and pack methods
Report presenting an apparatus for supporting a single thickness of sheet against buckling so that its compressive yield strength can be determined by the single-thickness method. The results of testing are compared with those from two other methods. This method results in substantial cost savings as compared to the pack method.
Date:
August 1941
Creator:
Paul, D. A.; Howell, F. M. & Grieshaber, H. E.
System:
The UNT Digital Library
A comparison of the aerodynamic characteristics of the normal and three reflexed airfoils in the variable density wind tunnel
"An investigation was made of the aerodynamic effects of reflexing the trailing edge of three commonly used airfoils. Six airfoils were used in the investigation: three having the normal profiles of the Navy 60, the Boeing 106, and the Gottingen 398, and three having these profiles modified to obtain a reflexed trailing edge with the mean camber line changed to give Cmc/4=0. The tests were conducted at a value of the Reynolds Number of approximately 3,100,000 in the variable density wind tunnel of the National Advisory Committee for Aeronautics. Measurements of lift, drag, and pitching moment were made on each of the six airfoils" (p. 1).
Date:
August 1931
Creator:
DeFoe, George L.
System:
The UNT Digital Library
Comparison of the Experimental Pressure Distribution on an NACA 0012 Profile at High Speeds With That Calculated by the Relaxation Method
Note presenting pressure-distribution measurements made on a 5-inch-chord NACA 0012 airfoil at zero angle of attack in the Langley rectangular high-speed tunnel, a 4- by 18-inch closed-throat tunnel, and compared with results calculated by Emmons for an equivalent airfoil-channel configuration by using the relaxation method.
Date:
August 1950
Creator:
Amick, James L.
System:
The UNT Digital Library
A comparison of the measured and predicted lateral oscillatory-characteristics of a 35 degree swept-wing fighter airplane
Report presenting results of a 35 degree swept-wing fighter airplane during lateral oscillations over a range of Mach numbers and pressure altitudes. Experimental and computed values for the period of the lateral oscillation and time required to damp to half amplitude are shown. Results regarding typical time histories, some of the data obtained, oscillatory characteristics, and flying characteristics are provided.
Date:
August 1955
Creator:
McNeill, Walter E. & Cooper, George E.
System:
The UNT Digital Library
A comparison of the results from general tank tests of 1/6- and 1/12-full-size models of the British Singapore IIC flying boat
From Summary: "A 1/6-full-size model of the hull of the British Singapore IIC flying boat was tested in the NACA tank. The results are given in the form of charts and are compared with the results of previous tests made in the NACA tank of a 1/12-full-size model, published in NACA T.N. No. 580, and with the results of tests made in the British R.A.E. tank of another 1/6-full-size model of the same hull. When the data from the tests of the 1/6- and 1/12-full-size models were compared on the basis of Froude's law of comparison, differences were found."
Date:
August 1942
Creator:
Truscott, Starr & Dawson, John R.
System:
The UNT Digital Library
A comparison of two methods for calculating transient temperatures for thick walls
Report presenting a comparison of two different methods of calculating transient temperatures for thick walls with arbitrary variation of heat-transfer coefficient and adiabatic-wall temperature.
Date:
August 1958
Creator:
Buglia, James J. & Brinkworth, Helen
System:
The UNT Digital Library
Compressibility Factor, Density, Specific Heat, Enthalpy, Entropy, Free-Energy Function, Viscosity, and Thermal Conductivity of Steam
Note presenting tables of thermal properties of stream that have been prepared in an NBS-NACA series. They include, for real gas, the compressibility factor, the density, the specific heat at constant pressure, the enthalpy, the entropy, the free-energy function, the viscosity, and the thermal conductivity.
Date:
August 1956
Creator:
Fano, Lilla; Hubbell, John H. & Beckett, Charles W.
System:
The UNT Digital Library
Compressible Flow Tables for Air
"A tabulation is presented of functions of the Mach number which are frequently used in high-speed aerodynamics. The tables include values of Mach number from 0 to 10.0 in increments of 0.01 and the functions are based on the assumption that air is a perfect gas having a specific-heat ratio of 1.400" (p. 1).
Date:
August 1948
Creator:
Burcher, Marie A.
System:
The UNT Digital Library
Compressible Laminar Flow and Heat Transfer About a Rotating Isothermal Disk
Note presenting a reexamination of the flow and heat transfer about a rotating isothermal disk to include the effects of compressibility and property variations. Results regarding velocities, temperatures, heat transfer, and skin friction and torque, are provided.
Date:
August 1958
Creator:
Ostrach, Simon & Thornton, Philip R.
System:
The UNT Digital Library
Compression-ignition engine performance with undoped and doped fuel oils and alcohol mixtures
From Summary: "Several fuel oils, doped fuel oils, and mixtures of alcohol and fuel oil were tested in a high-speed, single-cylinder, compression-ignition engine to determine power output, fuel consumption, and ignition and combustion characteristics. Fuel oils or doped fuel oils of high octane number had shorter ignition lags, lower rates of pressure rise, and gave smoother engine operation than fuel oils or doped fuel oils of low octane number."
Date:
August 1939
Creator:
Moore, Charles S. & Foster, Hampton H.
System:
The UNT Digital Library
Compressive and Torsional Buckling of Thin-Wall Cylinders in Yield Region
Note presenting a general set of equilibrium differential equations for the plastic buckling of cylinders, which are based on assumptions that have led to the best agreement between theory and test data on inelastic buckling of flat plates. Test data are presented which indicate satisfactory agreement with the theoretical plasticity-reduction factors in most cases. Some of the topics addressed include compressive buckling and torsional buckling.
Date:
August 1956
Creator:
Gerard, George
System:
The UNT Digital Library
Compressive Stress-Strain Properties of 17-7 PH and AM 350 Stainless-Steel Sheet at Elevated Temperatures
Note presenting compressive stress-strain test results for 17-7 PH and AM 350 stainless-steel sheet in the heat-treated and annealed conditions for temperatures from room temperature to 1200 degrees Fahrenheit. Representative stress-strain curves are given for both materials at the test temperatures.
Date:
August 1957
Creator:
Stein, Bland A.
System:
The UNT Digital Library
Compressive Tests of a Monocoque Box
"A monocoque box specimen of aluminum alloy was subjected to end compression and the strains in the stringers were measured up to loads at which permanent set became noticeable. The stringer strains at low loads agreed closely with those computed from the assumption of uniform stress distribution. Buckling of the 0.026-inch sheet between stringers and of the 0.075-inch shear web took place at stresses in accord with theoretical values" (p. 1).
Date:
August 1939
Creator:
Ramberg, Walter; McPherson, Albert E. & Levy, Sam
System:
The UNT Digital Library
Considerations affecting the additional weight required in mass balance of ailerons
"This paper is essentially a consideration of mass balance of ailerons from a preliminary design standpoint, in which the extra weight of the mass counterbalance is the most important phase of the problem. Equations are developed for the required balance weight for a simple aileron and this weight is correlated with the mass-balance coefficient. It is concluded the location of the c.g. of the basic aileron is of paramount importance and that complete mass balance imposes no great weight penalty if the aileron is designed to have its c.g. inherently near to the hinge axis" (p. 1).
Date:
August 1937
Creator:
Diehl, W. S.
System:
The UNT Digital Library
A Correlation of Results of a Flight Investigation With Results of an Analytical Study of Effects of Wing Flexibility on Wing Strains Due to Gusts
Report presenting a study of the effects of wing flexibility on wing strains due to gusts for four spanwise stations of a four-engine bomber airplane and a correlation with previous testing results. Results regarding the power spectre, peak counts, amplification factors, statistical reliability, input disturbance, frequency-response functions, output response, and amplification factors are provided.
Date:
August 1957
Creator:
Shufflebarger, C. C.; Payne, Chester B. & Cahen, George L.
System:
The UNT Digital Library
Criterions for prediction and control of ram-jet flow pulsations
Report presenting the results of a theoretical and experimental study of ramjet diffuser flow pulsing, commonly referred to as a buzz condition, with and without combustion. The acoustical resonance properties of ram jets are an important factor in establishing the frequency of diffuser flow pulsations.
Date:
August 1955
Creator:
Sterbentz, William H. & Evvard, John C.
System:
The UNT Digital Library
Critical Combinations of Shear and Direct Axial Stress for Curved Rectangular Panels
"A solution is presented for the problem of the buckling of curved rectangular panels subjected to combined shear and direct axial stress. Charts giving theoretical critical combinations of shear and direct axial stress are presented for panels having five different length-width ratios. Because the actual critical compressive stress of rectangular panels having substantial curvature is known to be much lower than the theoretical value, a semiempirical method of analysis of curved panels subjected to combined shear and direct axial stress is presented for use in design" (p. 1).
Date:
August 1949
Creator:
Schildcrout, Murry & Stein, Manuel
System:
The UNT Digital Library
A Critical Review of Notch Sensitivity in Stress-Rupture Tests
Note presenting a review of English and German literature on notch stress-rupture data, which included the effect of notching on rupture strength in general, the effect of chemical composition and heat treatment on notch stress-rupture characteristics, the mechanism of stress-rupture embrittlement and notch sensitivity in low-alloy steels, and a comparison of the influence of notch geometry on notch strength in stress-rupture tests and in conventional tensile tests.
Date:
August 1951
Creator:
Brown, W. F., Jr. & Sachs, George
System:
The UNT Digital Library
Critical shear stress of an infinitely long plate in the plastic region
From Summary: "The plasticity reduction factor in the formula for the buckling stress of a long plate under uniform shear has been computed from the properties of the stress-strain curve for the material. Some limited tests on the shear buckling of 24S-0 aluminum-alloy plates in the plastic region tend to confirm the value of the reduction factor predicted by the theory. Restraint against rotation along the edges of the plate has little or no effect upon the value of the reduction factor according to theoretical calculation."
Date:
August 1948
Creator:
Stowell, Elbridge Z.
System:
The UNT Digital Library
Critical stress of plate columns
Report presenting solutions for the elastic buckling stress of flat rectangular plates with simply supported or fixed ends when loaded as columns. The procedure for determining the critical stress of plate columns with intermediate end fixities is also given.
Date:
August 1950
Creator:
Houbolt, John C. & Stowell, Elbridge Z.
System:
The UNT Digital Library