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Bending Tests of Metal Monocoque Fuselage Construction (open access)

Bending Tests of Metal Monocoque Fuselage Construction

Study of the bending stress in smooth skin, aluminum alloy, true monocoque fuselage sections of varying ratio of diameter to thickness.
Date: November 1930
Creator: Mossman, Ralph W. & Robinson, Russell G.
System: The UNT Digital Library
Corrugated Metal Diaphragms for Aircraft Pressure-Measuring Instruments (open access)

Corrugated Metal Diaphragms for Aircraft Pressure-Measuring Instruments

Note presenting a description of a large number of corrugated diaphragms of beryllium copper, phosphor bronze, and Z-nickel with geometrically similar outlines but various diameters and thicknesses were formed by hydraulic pressing. The apparatus and technique used in the manufacture, testing, and heat treatment are described. Results regarding pressure-deflection curves, load limit, effect of center reinforcing, snap-action diaphragms, deflection traverse, thickness variations, and concentrated central loads are provided.
Date: November 1939
Creator: Wildhack, W. A. & Goerke, V. H.
System: The UNT Digital Library
A preliminary study of a propeller powered by gas jets issuing from the blade tips (open access)

A preliminary study of a propeller powered by gas jets issuing from the blade tips

From Summary: "Computations are made of the performance of a propeller designed to develop 56 thrust horsepower at 100 miles per hour. The fuel consumption of the jet-operated propeller would be considerably higher than that of a reciprocating engine and a propeller. The lighter weight of the jet-operated propeller will result in a lighter weight of engine plus fuel for short-range flights. A theoretical analysis is made of a propeller powered by gas jets issuing from the blade tips."
Date: November 1946
Creator: Sanders, J. C. & Sanders, N. D.
System: The UNT Digital Library
Performance of Hoods for Aircraft Exhaust-Gas Turbines (open access)

Performance of Hoods for Aircraft Exhaust-Gas Turbines

Report presenting the performance of a turbosupercharger turbine with three types of exhaust hood. The results for conical hoods, flat-nozzle hoods, and short-turning-radius hoods are provided.
Date: November 1946
Creator: Turner, L. Richard; Lowdermilk, Warren H. & Lord, Albert M.
System: The UNT Digital Library
Friction Coefficients in the Inlet Length of Smooth Round Tubes (open access)

Friction Coefficients in the Inlet Length of Smooth Round Tubes

Note presenting an experimental study of friction coefficients near the inlet of smooth, round tubes with bellmouth entrances. Four different combinations of approach section and bellmouth entry were used. Results regarding the apparent local friction coefficient, integrated friction coefficient, effect of induced turbulence, laminar inlet zone, developed friction coefficient, and application to discharge coefficients for rounded-entrance flow nozzles are provided.
Date: November 1948
Creator: Shapiro, Ascher H. & Smith, R. Douglas
System: The UNT Digital Library
Tests on Duralumin Columns for Aircraft Construction (open access)

Tests on Duralumin Columns for Aircraft Construction

The following paper is based on the results of tests, upon duralumin columns, contained in two theses presented to the Department of Civil and Sanitary Engineering of the Massachusetts Institute of Technology.
Date: November 1924
Creator: Lee, John G.
System: The UNT Digital Library
On possible similarity solutions for three-dimensional incompressible laminar boundary layers 2: similarity with respect to stationary polar coordinates (open access)

On possible similarity solutions for three-dimensional incompressible laminar boundary layers 2: similarity with respect to stationary polar coordinates

From Summary: "Solutions of mainstream flow patterns for three-dimensional, laminar, incompressible thin-boundary-layer flows (over flat or slightly curved surfaces) having similarity with respect to stationary polar coordinates in the plane of the surface are derived. The solutions are summarized in a table."
Date: November 1956
Creator: Herzig, Howard Z. & Hansen, Arthur G.
System: The UNT Digital Library
Stability Limits and Burning Velocities of Laminar Hydrogen-Air Flames at Reduced Pressure (open access)

Stability Limits and Burning Velocities of Laminar Hydrogen-Air Flames at Reduced Pressure

Note presenting laminar burning velocity measured at pressures of 1 atmosphere and below and critical boundary velocity gradient for flashback at pressures below 1 atmosphere over a range of compositions for hydrogen-air burner flames. Pressure exponents of 0.23 for burning velocity and 1.35 for flashback velocity gradient was found. Results regarding blowoff and general stability loop, burning velocity, relations among various combustion properties, and reaction order from pressure exponents are provided.
Date: November 1956
Creator: Fine, Burton
System: The UNT Digital Library
A velocity-correction formula for the calculation of transonic Mach number distributions over diamond-shaped airfoils (open access)

A velocity-correction formula for the calculation of transonic Mach number distributions over diamond-shaped airfoils

Report presenting a velocity-correction formula for the purpose of calculating, from the known Mach number distribution for a diamond-shaped airfoil at a stream Mach number of 1.0, Mach number distributions on the same airfoil at speeds from a Mach number of about 0.8 to shock-attachment Mach number. An expression for the rate of change of local Mach number with stream Mach number is derived and an explicit equation for the drag coefficient as a function of stream Mach number and thickness ratio is given.
Date: November 1951
Creator: Ivey, H. Reese & Harder, Keith C.
System: The UNT Digital Library
Effect of taper ratio on the low-speed rolling stability derivatives of swept and unswept wings of aspect ratio 2.61 (open access)

Effect of taper ratio on the low-speed rolling stability derivatives of swept and unswept wings of aspect ratio 2.61

Results of tests conducted in the 6-foot-diameter rolling-flow test section of the Langley stability tunnel to determine the effects of varying taper ratio on the rolling and static stability characteristics of a swept wing are presented; results are also given for the effects of varying taper ratio on an unswept wing and for the effects of sweep on a tapered wing. All the models were of aspect ratio 2.61 and had NACA 0012 sections normal to the quarter-chord line. Taper ratios of 1.00, 0.50, and 0.25 and sweep angles of 0 degrees and 45 degrees were investigated.
Date: November 1951
Creator: Brewer, Jack D. & Fisher, Lewis R.
System: The UNT Digital Library
Heat Capacity Lag in Gases (open access)

Heat Capacity Lag in Gases

Note presenting a review of the literature on the sonic studies of the problem of the excitation of molecular vibrations by collision. The theory on which the interpretation of almost all the sonic work has been based is discussed rather qualitatively in some detail. Results concerning techniques, principal experimental programs, and an interpretation of the results are provided.
Date: November 1951
Creator: Walker, Richard
System: The UNT Digital Library
Experimental Investigation at Low Speed of the Effects of Wing Position on the Static Stability of Models Having Fuselages of Various Cross Section and Unswept and 45 Degrees Sweptback Surfaces (open access)

Experimental Investigation at Low Speed of the Effects of Wing Position on the Static Stability of Models Having Fuselages of Various Cross Section and Unswept and 45 Degrees Sweptback Surfaces

Note presenting an investigation to determine the effects of wing position on the low-speed static longitudinal and static lateral stability of airplane models with fuselages of square and rectangular cross sections and unswept and 45 degree sweptback surfaces. The results of the investigation indicated that at low angles of attack, the complete unswept models with the wing in the high position were more stable or least longitudinally unstable. The results also showed that wing-fuselage interference causes an increase in effective dihedral angle when the wing is moved to the high position.
Date: November 1956
Creator: Letko, William
System: The UNT Digital Library
Langley full-scale-tunnel investigations of the maximum-lift and stalling characteristics of a trapezoidal wing of aspect ratio 4 with circular-arc airfoil sections (open access)

Langley full-scale-tunnel investigations of the maximum-lift and stalling characteristics of a trapezoidal wing of aspect ratio 4 with circular-arc airfoil sections

Report presenting an investigation of the results at high Reynolds numbers and low Mach numbers to determine the maximum-lift and stalling characteristics of an aspect-ratio-4 trapezoidal wing with 10-percent-thick, circular-arc airfoil sections. Testing occurred measurements of lift, drag, and pitching-moment coefficients of the basic wing and of the wing with 0.20-chord droop-nose and rear flaps deflected alone and in combination with one another.
Date: November 1952
Creator: Lange, Roy H.
System: The UNT Digital Library
Effects of independent variations of mach number and reynolds number on the maximum lift coefficients of four NACA 6-series airfoil sections (open access)

Effects of independent variations of mach number and reynolds number on the maximum lift coefficients of four NACA 6-series airfoil sections

Report presenting an investigation in the low-turbulence pressure tunnel to determine the effects of Mach and Reynolds number on the maximum lift characteristics of the NACA 65-006, 64-009, 64-210, and 64(sub 2)-215 airfoil sections in smooth and leading-edge roughness conditions. A range of Mach and Reynolds numbers were explored.
Date: November 1952
Creator: Racisz, Stanley F.
System: The UNT Digital Library
Studies on Von Kármán's Similarity Theory and Its Extension to Compressible Flows: A Critical Examination of Similarity Theory for Incompressible Flows (open access)

Studies on Von Kármán's Similarity Theory and Its Extension to Compressible Flows: A Critical Examination of Similarity Theory for Incompressible Flows

Note presenting an investigation of three theories: the momentum transfer theory of Prandtl, the vorticity transfer theory of Taylor, and the similarity theory of Von Kármán. The primary focus is to examine Von Kármán's theory using modern concepts.
Date: November 1951
Creator: Lin, C. C. & Shen, S. F.
System: The UNT Digital Library
Studies of Von Kármán's Similarity Theory and Its Extension to Compressible Flows: A Similarity Theory for Turbulent Boundary Layer Over a Flat Plate in Compressible Flow (open access)

Studies of Von Kármán's Similarity Theory and Its Extension to Compressible Flows: A Similarity Theory for Turbulent Boundary Layer Over a Flat Plate in Compressible Flow

Note presenting a treatment of the problem of turbulent boundary layer over a flat plate in compressible flow. The dissipation term in the energy equation, often neglected, is first carefully studied and found to be of importance. The four main approximations include the turbulence pattern, the boundary-layer growth, the two choices of the length scale, and the effect of pressure gradient.
Date: November 1951
Creator: Lin, C. C. & Shen, S. F.
System: The UNT Digital Library
Studies of Von Kármán's Similarity Theory and Its Extension to Compressible Flow: Investigation of Turbulent Boundary Layer Over a Flat Plate in Compressible Flow by the Similarity Theory (open access)

Studies of Von Kármán's Similarity Theory and Its Extension to Compressible Flow: Investigation of Turbulent Boundary Layer Over a Flat Plate in Compressible Flow by the Similarity Theory

Note presenting an investigation of the turbulent-boundary-layer flow over a flat plate in compressible flow. The report shows how the influence of the Mach number can be predicted from the theory after the constant coefficients in the theory are determined by one set of experimental measurements. By averaging the Navier-Stokes equations, differential equations for the mean flow are obtained.
Date: November 1951
Creator: Shen, S. F.
System: The UNT Digital Library
Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds (open access)

Aerodynamic characteristics and flying qualities of a tailless triangular-wing airplane configuration as obtained from flights of rocket-propelled models at transonic and supersonic speeds

Report discussing a flight investigation of rocket-powered models of a tailless triangular-wing airplane configuration was made through the transonic and low supersonic speed range at the Langley Pilotless Aircraft Research Station at Wallops Island, Va. An analysis of the aerodynamic coefficients, stability derivatives, and flying qualities based on the results obtained from the successful flight tests of three models is presented.
Date: November 1956
Creator: Mitcham, Grady L.; Stevens, Joseph E. & Norris, Harry P.
System: The UNT Digital Library
Application of Variational Methods to Transonic Flows With Shock Waves (open access)

Application of Variational Methods to Transonic Flows With Shock Waves

Note presenting a modification of certain variational methods for the approximate solution of subsonic and transonic flows to compensate for the fact that those methods fail as soon as shock waves occur. By applying a variational principle to the regions of flow behind shock waves and Bateman's original principle to the other regions in the fluid, shock equations can be directly obtained.
Date: November 1951
Creator: Wang, Chi-Teh & Chou, Pei-Chi
System: The UNT Digital Library
Hydrodynamic Investigation of a Series of Hull Models Suitable for Small Flying Boats and Amphibians (open access)

Hydrodynamic Investigation of a Series of Hull Models Suitable for Small Flying Boats and Amphibians

Note presenting the results of an investigation to obtain hydrodynamic information on a series of hull models suitable for small flying boats or amphibians of from 2000 to 5000 pounds gross weight. The series of hulls consisted of a basic hull with simple lines, and of plus and minus variations to the design in which the beam, stern-post angle, and afterbody length were altered. The results show that it is possible to design a hull with simple lines that will be suitable for small flying boats or amphibians.
Date: November 1951
Creator: Hugli, W. C., Jr. & Axt, W. C.
System: The UNT Digital Library
Application of Response Function to Calculation of Flutter Characteristics of a Wing Carrying Concentrated Masses (open access)

Application of Response Function to Calculation of Flutter Characteristics of a Wing Carrying Concentrated Masses

Note presenting concepts involved in the harmonic-response-function method, such as the direct or conjugate characteristic modes, by application of the method to the calculation of the change in flutter characteristics of a wing due to adding concentrated masses.
Date: November 1951
Creator: Serbin, H. & Costilow, E. L.
System: The UNT Digital Library
Investigation of deflectors as gust alleviators on a 0.09-scale model of the Bell X-5 airplane with various wing sweep angles from 20 degrees to 60 degrees at Mach numbers from 0.40 to 0.90 (open access)

Investigation of deflectors as gust alleviators on a 0.09-scale model of the Bell X-5 airplane with various wing sweep angles from 20 degrees to 60 degrees at Mach numbers from 0.40 to 0.90

Report presenting an investigation in the high-speed 7- by 10-foot tunnel to determine the effectiveness of a given deflector arrangement as a gust alleviator on a model of the Bell X-5 airplane with various wing sweep angles, Mach numbers, and angles of attack. Results regarding lift, drag, and pitching moment are provided.
Date: November 1957
Creator: Croom, Delwin R. & Huffman, Jarrett K.
System: The UNT Digital Library
Flight measurements of drag and base pressure of a fin-stabilized parabolic body of revolution (NACA RM-10) at different Reynolds numbers and at Mach numbers from 0.9 to 3.3 (open access)

Flight measurements of drag and base pressure of a fin-stabilized parabolic body of revolution (NACA RM-10) at different Reynolds numbers and at Mach numbers from 0.9 to 3.3

From Summary: "Free-flight tests have been made to investigate the total drag and base drag at different Reynolds numbers of full-scale and half-scale models of an NACA research model designated the RM-10. The general shape of the body was a parabola of revolution of fineness ratio 12.2 with a blunt base to provide space for the rocket jet. The models were stabilized by four 60 degree sweptback fins mounted at the base of the bodies."
Date: November 1954
Creator: Jackson, H. Herbert; Rumsey, Charles B. & Chauvin, Leo T.
System: The UNT Digital Library
Viscosity Corrections to Cone Probes on Rarefied Supersonic Flow at a Nominal Mach Number of 4 (open access)

Viscosity Corrections to Cone Probes on Rarefied Supersonic Flow at a Nominal Mach Number of 4

Note presenting data obtained for the viscosity corrections to cone probes in supersonic rarefied air flow at a nominal Mach number of 4. The test models consisted of a set of seven geometrically similar 5 degree semivertex-angle cones. Results regarding cone surface pressure distributions, calibration data for geometrically similar cones, orifices size effect, and tests at other Mach numbers are provided.
Date: November 1954
Creator: Talbot, L.
System: The UNT Digital Library