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347 Matching Results
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Comparison between experimental and predicted downwash at a Mach number of 0.25 behind a wing-body combination having a triangular wing of aspect ratio of 2.0
A study to evaluate a method for predicting the downwash in a transverse plane behind a wing-body combination throughout a range of angles of attack. The wing-body combination had a ratio of maximum body diameter to wing span of 0.259, a triangular wing with an aspect ratio of 2.0, and a body of revolution with a fineness ratio of 12.5. Results regarding span loading, downwash, and vortex cores are provided.
Date:
May 1956
Creator:
Sorensen, Norman E. & Hopkins, Edward J.
System:
The UNT Digital Library
Static longitudinal and lateral stability characteristics at low speed of unswept-midwing models having wings with an aspect ratio of 2, 4, or 6
Report presenting an investigation to determine the effects of the various components and combinations of components on the static longitudinal and lateral stability characteristics of unswept-midwing models having wings with a variety of aspect ratios for a range of angles of attack. Results regarding static longitudinal stability characteristics and static lateral stability characteristics are provided.
Date:
May 1956
Creator:
Wolhart, Walter D. & Thomas, David F., Jr.
System:
The UNT Digital Library
Investigation at zero forward speed of a leading-edge slat as a longitudinal control device for vertically rising airplanes that utilize the redirected-slipstream principle
Report presenting an investigation of a leading-edge slat as a possible longitudinal control device for vertically rising airplanes that utilize the redirected-slipstream principle at zero forward speed in a static-thrust facility. A semispan wing model equipped with large-chord slotted flaps and two large-diameter overlapping propellers was used. Results regarding the effect of slat position, effect of propeller position, characteristics of the modified model, and a comparison of characteristics with one or two propellers are provided.
Date:
May 1956
Creator:
Kuhn, Richard E.
System:
The UNT Digital Library
Bending Stresses Due to Torsion in a Tapered Box Beam
Note presenting a method for the calculation of bending stresses due to torsion in a tapered box beam. A special taper was assumed in which all flanges, if extended, would meet at a point. The results obtained by this method were compared with experimental data obtained from tests performed on a tapered box beam.
Date:
May 1947
Creator:
Kruszewski, Edwin T.
System:
The UNT Digital Library
Effect of spoiler-type lateral-control devices on the twisting moments of NACA 230-Series airfoil sections
Report presenting an investigation of the effects of several spoiler arrangements on the spanwise variation of section twisting moments of a wing of NACA 230-series airfoil sections. Both plain and perforated spoilers were tested at a designated Mach and Reynolds number and force and moment measurements as well as chordwise pressure-distribution measurements at six spanwise stations were obtained.
Date:
May 1947
Creator:
Fitzpatrick, James E. & Furlong, G. Chester
System:
The UNT Digital Library
Effects of Mach Number and Reynolds Number on the Maximum Lift Coefficient of a Wing of NACA 230-Series Airfoil Sections
Wing was tested with full-span, partial-span, or split flaps deflected 60 Degrees and without flaps. Chordwise pressure-distribution measurements were made for all flap configurations.. Peak values of maximum lift coefficient were obtained at relatively low free-stream Mach numbers and, before critical Mach number was reached, were almost entirely dependent on Reynolds Number. Lift coefficient increased by increasing Mach number or deflecting flaps while critical pressure coefficient was reached at lower free-stream Mach numbers.
Date:
May 1947
Creator:
Furlong, G. Chester & Fitzpatrick, James E.
System:
The UNT Digital Library
Column Strength of Aluminum Alloy 14S-T Extruded Shapes and Rod
Note presenting an investigation of the use of aluminum alloy 14S-T in heavy-duty structural applications and aircraft. The column data presented in this report have been obtained on extruded shapes and on rolled and drawn rod of the alloy.
Date:
May 1946
Creator:
Leary, J. R. & Holt, Marshall
System:
The UNT Digital Library
A transonic propeller of triangular plan form
Report presenting a proposal for the isosceles triangle twisted into a screw surface about its axis as a propeller for transonic flight speeds. The purpose is to attain the drag reduction associated with a large sweepback in a structurally practicable configuration.
Date:
May 1947
Creator:
Ribner, Herbert S.
System:
The UNT Digital Library
A summary of diagonal tension Part 1: methods of analysis
Previously published methods for stress and strength analysis of plane and curved shear webs working in diagonal tension are presented as a unified method. The treatment is sufficiently comprehensive and detailed to make the paper self-contained. Part 1 discusses the theory and methods for calculating the stresses and shear deflections of web systems as well as the strengths of the web, the stiffeners, and the riveting. Part 2, published separately, presents the experimental evidence. (author).
Date:
May 1952
Creator:
Kuhn, Paul; Peterson, James P. & Levin, L. Ross
System:
The UNT Digital Library
A summary of diagonal tension Part 2: experimental evidence
Report presenting the experimental evidence regarding the analysis of web systems working in diagonal tension given in Part I of the paper.
Date:
May 1952
Creator:
Kuhn, Paul; Peterson, James P. & Levin, L. Ross
System:
The UNT Digital Library
Investigation of Effect of Span, Spanwise Location, and Chordwise Location of Spoilers on Lateral Control Characteristics of a Tapered Wing
Note presenting a wind-tunnel investigation of the effect of span, spanwise location, and chordwise location of spoilers on the lateral control characteristics of an unflapped semispan wing equipped with a simple spoiler with a projection 5 percent of the chord. The chordwise investigation involved moving a 50-percent-semispan spoiler from the 50-percent-chord station to the 80-percent-chord station. Results regarding the plain-wing characteristics, spanwise investigation, and chordwise investigation are provided.
Date:
May 1947
Creator:
Fischel, Jack & Tamburello, Vito
System:
The UNT Digital Library
Wind-Tunnel Investigation of the Air Load Distribution on Two Combinations of Lifting Surface and Fuselage
Report presenting wind tunnel measurements of the air load distribution on a canard-type model. Two combinations of lifting surface and fuselage were obtained by removing the wing and stabilizer of the model. Results regarding the fuselage pressure distribution, spanwise loading curves, and variation of lift, drag, and pitching-moment coefficients with angle of attack are provided.
Date:
May 1947
Creator:
Sandahl, Carl A. & Vollo, Samuel D.
System:
The UNT Digital Library
Wind-tunnel investigation of the effects of surface-covering distortion on the characteristics of a flap having undistorted contour maintained for various distances ahead of the trailing edge
Report presenting tests of a modified NACA 65(sub 1)-012 airfoil with a 30-percent airfoil-chord flap with contours simulating various distorted surface-covering shapes for the purpose of investigating practicability of reducing distortion effects to a negligible amount by maintaining an undistorted contour over a small part of the flap chord.
Date:
May 1947
Creator:
Toll, Thomas A.; Queijo, M. J. & Brewer, Jack D.
System:
The UNT Digital Library
Comparison of Static Strengths of Machine Countersunk Riveted Joints in 24S-T, X75S-T, and Alclad 75S-T Sheet
Note presenting static tests made on machine-countersunk riveted joints in 24S-T, X75S-T, and Alclad 75S-T sheet using A17S-T and 24S-T rivets. In order to intensify the cutting action of the rivets, all specimens were made with the depth of countersink just equal to the thickness of the sheet.
Date:
May 1946
Creator:
Hartmann, E. C. & Zamboky, A. N.
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.
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.
System:
The UNT Digital Library
Wing-tunnel investigation of effects of forward movements of transition on section characteristics of a low-drag airfoil with a 0.24-chord sealed plain aileron
Report presenting an investigation to determine the effects of forward movements of transition on the section characteristics of a 12-percent-thick low-drag airfoil section with a 0.24-chord sealed plain aileron. Section lift and aileron section hinge-moment and seal-pressure characteristics were determined at a specific Reynolds number for aerodynamically smooth surfaces and with fixed transition at two different points.
Date:
May 1948
Creator:
Racisz, Stanley F. & Cahill, Jones F.
System:
The UNT Digital Library
An improved approximate method for calculating lift distributions due to twist
Report presenting a method for calculating the lift distribution due to twist which gives a closer approximation than the current Schrenk empirical method and requires about the same amount of computing. The method uses the lifting-line theory and makes use of the lift distribution due to angle of attack and considers the aspect ratio of the wing. Examples are presented for four main types of twist: symmetrical, antisymmetrical, continuous, and discontinuous.
Date:
May 24, 1950
Creator:
Sivells, James C.
System:
The UNT Digital Library
A survey of the aircraft-noise problem with special reference to its physical aspects
Report presenting a background for various general phases of the aircraft-noise problem. The effects of noise are discussed and brief discussions of the physical characteristics of aircraft noise and some ways of protection from noise are included, as well as a bibliography of research related to the noise problem. At the time of this report, no easy and inexpensive solution to the aircraft-noise problem is currently available.
Date:
May 1952
Creator:
Hubbard, Harvey H.
System:
The UNT Digital Library
Effect of High-Lift Devices on the Low-Speed Static Lateral and Yawing Stability Characteristics of an Untapered 45 Degrees Sweptback Wing
Results of a low-speed wind-tunnel investigation to determine the effect of high-lift devices on the static lateral stability derivatives and the yawing derivatives of an untapered 45 degrees sweptback wing are presented. The tests were made in the curved-flow test section of the Langley stability tunnel at a Reynolds number of 1.1 X 10 to the sixth power.
Date:
May 1952
Creator:
Lichtenstein, Jacob H.
System:
The UNT Digital Library
Electrical Techniques for Compensation of Thermal Time Lag of Thermocouples and Resistance Thermometer Elements
Note presenting a description of basic electrical networks that compensate for the thermal time lag of thermocouple and resistance thermometer elements used in combustion research and in the control of jet power plants. The measurement or the detection of rapid temperature changes by use of such elements can thereby be improved.
Date:
May 6, 1952
Creator:
Shepard, Charles E. & Warshawsky, Isidore
System:
The UNT Digital Library
Effect of changing passage configuration on internal-flow characteristics of a 48-inch centrifugal compressor 1: Change in blade shape
Report presenting a modification of the passage contour of a 48-inch centrifugal impeller by changing the shape of the blades with the objective of reducing the deceleration rates along the blade faces and thereby improving the internal efficiency of the impeller. The modified impeller was found to show a general improvement in efficiency throughout the passage over that of the original impeller.
Date:
May 1952
Creator:
Michel, Donald J.; Mizisin, John & Prian, Vasily
System:
The UNT Digital Library
Some Considerations of the Lateral Stability of High-Speed Aircraft
Note presenting an investigation to determine the effect of variations in the lateral-stability derivatives, wing loading, altitude, and radii of gyration on the combination of directional stability and effective dihedral required for lateral stability at the landing and cruising condition. The results of the investigation showed that an airplane with a high wing loading designed for high-speed and high-altitude flight would be laterally stable if the moments of inertia, the location of the principal longitudinal axis of the airplane, and the value of the damping-in-roll derivative were properly selected.
Date:
May 1947
Creator:
Sternfield, Leonard
System:
The UNT Digital Library
The Langley Two-Dimensional Low-Turbulence Pressure Tunnel
"A description is presented of the Langley two-dimensional low-turbulence pressure tunnel and a history is given of the work done at the Langley Memorial Aeronautical Laboratory which led to the achievement of a remarkably low level of turbulence in the air stream of this wind tunnel. The types of investigations to which the tunnel is suited and the methods of obtaining and correcting data are also discussed" (p. 1).
Date:
May 1947
Creator:
von Doenhoff, Albert E. & Abbott, Frank T., Jr.
System:
The UNT Digital Library