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Analytical investigation of acceleration restriction in a fighter airplane with an automatic control system
From Introduction: "In the present report, consideration is given to certain features intended to improve the accleration-limiting characteristics of a normal-accleration control system."
Date:
January 1958
Creator:
Matthews, James T., Jr.
System:
The UNT Digital Library
Contribution of the wing panels to the forces and moments of supersonic wing-body combinations at combined angles
Report presenting a wind-tunnel investigation at Mach number 1.96 to determine the normal forces, pitching moments, and rolling moments contributed by each wing panel of a cruciform-wing and body combination over a wide range of combined angles of pitch and roll. The wings were triangular of aspect ratio 2 and the body was an ogive-cylinder combination. Results regarding individual panels and panel combinations are provided.
Date:
January 1958
Creator:
Spahr, J. Richard
System:
The UNT Digital Library
A Correlation of Results of Flight Investigation With Results of an Analytical Study of Effects of Wing Flexibility on Wing Strains Due to Gusts
An analytical study of the effects of wing flexibility on wing strains due to gusts has been made for four spanwise stations of a four-engine bomber airplane, and the results have been correlated with results of a previous flight investigation.
Date:
1958
Creator:
Shufflebarger, C. C.; Payne, Chester B. & Cahen, George L.
System:
The UNT Digital Library
Corrosion Resistance of Nickel Alloys in Molten Sodium Hydroxide
Note presenting a study of the corrosion resistance of 11 nickel-base compositions to molten sodium hydroxide at 1500 and 1700 degrees Fahrenheit in order to find a container material for the caustic at these temperatures. Results are provided for the solid-solution alloys, nickel with mechanically dispersed second phase materials, and the precipitation-hardened alloy.
Date:
January 1958
Creator:
Probst, H. B.; May, C. E. & McHenry, Howard T.
System:
The UNT Digital Library
Discrete Potential Theory for Two-Dimensional Laplace and Poisson Difference Equations
Note presenting a method for solving problems associated with Laplace and Poisson equations which, in general, requires considerably fewer equations than the usual methods and which gives a convergent solution by the method of successive approximations.
Date:
January 1958
Creator:
Saltzer, Charles
System:
The UNT Digital Library
Effect of angle of attack and thickness on aerodynamic coefficients of a rigid wing oscillating at very low frequencies in two-dimensional supersonic flow
Report presenting an analytical expression for the lift and pitching-moment coefficients of a wing of finite thickness performing a plunging motion and rotary oscillations about some fixed angle of attack at very low frequencies in two-dimensional flow. Calculated lift and pitching-moment coefficients and design charts are presented.
Date:
January 1958
Creator:
Malvestuto, Frank S., Jr. & Goodwin, Julia M.
System:
The UNT Digital Library
Effect of Environments of Sodium Hydroxide, Air, and Argon on the Stress-Rupture Properties of Nickel at 1500 Degrees F
Note presenting the stress-rupture properties of commercially pure nickel at 1500 degrees Fahrenheit as determined for its application as a container material for molten sodium hydroxide. Stress-rupture tests of L-nickel tubes containing sodium hydroxide were run with atmospheres of air or argon external to the tubes. Sodium hydroxide was found to have little effect on the stress-rupture strength of nickel tubes tested in argon at 1500 degrees Fahrenheit for times up to 200 hours.
Date:
January 1958
Creator:
McHenry, Howard T. & Probst, H. B.
System:
The UNT Digital Library
Effect of Flow Incidence and Reynolds Number on Low-Speed Aerodynamic Characteristics of Several Noncircular Cylinders With Applications to Directional Stability and Spinning
Note presenting the aerodynamic characteristics of several noncircular two-dimensional cylinders with axes normal to the stream at various flow incidences for a range of Reynolds numbers as determined from low-speed wind-tunnel tests. The results indicate that these parameters have large effects on the drag and side force developed on these cylinders. Results regarding drag of two-dimensional cylinders, side force developed on two-dimensional cylinders, and directional stability and spinning characteristics of three-dimensional bodies are provided.
Date:
January 1958
Creator:
Polhamus, Edward C.
System:
The UNT Digital Library
Effect of oxygen recombination on one-dimensional flow at high Mach numbers
Report presenting a theoretical analysis of air flow in a channel in which oxygen dissociation and recombination occur. An investigation is also made of the comparative relaxation times of the oxygen dissociation-recombination reaction in relation to molecular vibrations.
Date:
January 1958
Creator:
Heims, Steve P.
System:
The UNT Digital Library
Effect of temperature on rolling-contact fatigue life with liquid and dry powder lubricants
Report presenting an investigation of the effect of temperature using di(2-ethylhexyl) sebacate lubricant and dry powder lubricants on rolling-contact fatigue life on AISI M-1 tool-steel balls in the rolling-contact fatigue spin rig at maximum theoretical Hertz stress levels of 650,000 and 725,000 pounds per square inch in compression.
Date:
January 1958
Creator:
Carter, Thomas L.
System:
The UNT Digital Library
Effects of Airplane Flexibility on Wing Strains in Rough Air at 35,000 Feet as Determined by a Flight Investigation of a Large Swept-Wing Airplane
A flight investigation was made on a large sweptback-wing bomber airplane and the results are compared with data previously obtained at low altitude (5,000 feet). The effects of wing flexibility on the wing strains were, on the average, about 20 percent larger at the higher altitude.
Date:
January 1958
Creator:
Rhyne, Richard H.
System:
The UNT Digital Library
Experimental investigation of the effects of some shroud design variables on the static thrust characteristics of a small-scale shrouded propeller submerged in a wing
Report presenting an experimental investigation to determine the effects of shroud-lip radius of curvature, shroud length, and shroud diffuser angle on the static thrust characteristics of a small-scale shrouded propeller which simulated a propeller submerged in the wing of an airplane. Results regarding the effect of propeller blade angle, effect of lip radius, effect of propeller location in shroud, effect of shroud length behind the propeller plane, effect of diffuser angle, and effect of ground proximity are provided.
Date:
January 1958
Creator:
Taylor, Robert T.
System:
The UNT Digital Library
Experimental Investigation of the Lateral Trim of a Wing-Propeller Combination at Angles of Attack Up to 90 Degrees With All Propellers Turning in the Same Direction
Note presenting an experimental investigation to study the feasibility, from considerations of lateral trim, of having all the propellers of a tilting-wing vertical-take-off-and-landing (VTOL) airplane rotate in the same direction since this is a desirable feature from practical considerations. The model was a wing with four propellers, the slipstream from which covered practically the entire span of the wing. Results regarding basic data and application of the data are provided.
Date:
January 1958
Creator:
Newsom, William A., Jr.
System:
The UNT Digital Library
Experimental Investigation of Turbojet-Engine Multiple-Loop Controls for Non-Afterburning and Afterburning Modes of Engine Operation
Report presenting an experimental investigation of turbojet engine performance with several configurations of interacting multiple-loop controls in order to determine the ideal mode of control for optimum rotor speed and turbine-discharge temperature during thrust increase and afterburner ignition conditions.
Date:
January 1958
Creator:
Kirsch, Donald B.; Wenzel, Leon M. & Hart, Clint E.
System:
The UNT Digital Library
Fatigue Behavior of Aircraft Structural Beams
Report presenting an investigation of the correlation of composite structural fatigue behavior, basic material, and simple-element behavior. Fatigue and static testing were made on aluminum-alloy box beams and I-beams and on elements simulating key failure locations in the two beams.
Date:
January 1958
Creator:
Hyler, W. S.; Popp, H. G.; Gideon, D. N.; Gordon, S. A. & Grover, H. J.
System:
The UNT Digital Library
A Flight Investigation of the Effects of Varied Lateral Damping on the Effectiveness of a Fighter Airplane as a Gun Platform
Flight tests were conducted at three conditions of damping and two atmospheric turbulence levels with fixed-reticle, gyro computing, and telescopic gunsights. Results of simulated strafing runs indicate that the gun-line dispersion could be expected to be decreased about 7 percent by increased lateral damping and to be increased about 85 percent by decreased damping and about 40 percent by rough air of the type encountered. Use of the telescopic sight indicated a 20-percent decrease in gun-line dispersion.
Date:
January 1958
Creator:
Kuehnel, Helmut A.; Beckhardt, Arnold R. & Champine, Robert A.
System:
The UNT Digital Library
Flight Tests of Two Smoke-Producing Devices Having Deacon Rocket Boosters
"Two smoke-producing models having Deacon rocket boosters were flown at the Pilotless Aircraft Research Station at Wallops Island, Va. to test the functioning of the models and to obtain trajectory and drag data. The maximum drag coefficient for the first model was 1.19. Modifications of the launching lugs were made on the second model in order to obtain lower drag, and a maximum drag coefficient of 1.00 was obtained for this model. The length of the smoke trail obtained was about 43,000 feet for the first model and about 44,000 feet for the second model" (p. 1).
Date:
1958
Creator:
Lanford, Wade E.
System:
The UNT Digital Library
Lift and Moment on Thin Arrowhead Wings with Supersonic Edges Oscillating in Symmetric Flapping and Roll and Application to the Flutter of an All-Moveable Control Surface
Note presenting a theoretical treatment for determining lift and moment on thin arrowhead or pointed-tip wings of which the delta plan form is a special case with an unswept trailing edge. Expressions have been developed for the section and total forces and moments to the third power of the reduced frequency. Sample results are given in the form of curves to show that retention of terms to the third power of the frequency gives good accuracy over a range of frequency that covers many practical flutter applications.
Date:
January 1958
Creator:
Cunningham, H. J.
System:
The UNT Digital Library
Low-speed cascade investigation of compressor blades having loaded leading edges
Report presenting six-percent-thick NACA 63-series compressor-blade sections with a loaded-leading-edge mean line investigated systematically in a two-dimensional porous-wall cascade over a range of Reynolds numbers. Blades cambered to have four different isolated-airfoil lift coefficients were tested over the usable angle-of-attack range at four different inlet-air angles and two different solidities.
Date:
January 1958
Creator:
Emery, James C.
System:
The UNT Digital Library
A Low-Speed Experimental Investigation of the Effect of a Sandpaper Type of Roughness on Boundary-Layer Transition
Report describing the effects of an area of roughness on the velocity and turbulence measurements of an airfoil. It details the effects of the size, location, and height of the roughness on the Reynolds number. From Summary: "An investigation was made in the Langley low-turbulence pressure tunnel to determine the effect of size and location of a sandpaper type of roughness on the Reynolds number for transition."
Date:
1958
Creator:
Horton, Elmer A. & von Doenhoff, Albert E.
System:
The UNT Digital Library
Low-speed yawed-rolling characteristics and other elastic properties of a pair of 40-inch-diameter, 14-ply-rating, type VII aircraft tires
Report presenting the low-speed yawed-rolling characteristics of two 40 x 12, 14-ply-rating, type VII aircraft under straight-yawed rolling over a range of inflation pressures and yaw angles for two vertical loadings. Static testing was performed to determine the vertical, lateral, torsional, and fore-and-aft elastic characteristics of tires. Measured lateral and torsional spring constants appeared to decrease with increasing amplitude of tire lateral distortion or twist.
Date:
January 1958
Creator:
Horne, Walter B. & Smiley, Robert F.
System:
The UNT Digital Library
Low-Temperature, Vapor-Phase Oxidation of Fuel-Rich Hydrocarbon Mixtures
Note presenting a study of the vapor-phase oxidation of methylcyclohexane in a flow system in the temperature range of 300 to 400 degrees Celsius under the conditions of 0.1 the stoichiometric amount of oxygen, a contact time of 8 seconds, and a spiral Pyrex reactor 10.5 inches long with an inside diameter of 3/32 inch. The yields of acids, aldehydes, ketones, hydrogen peroxide, organic peroxides, olefin, water, and unreacted hydrocarbon were determined in the products.
Date:
January 1958
Creator:
House, William T. & Orchin, Milton
System:
The UNT Digital Library
A method for calculation of hydrodynamic lift for submerged and planing rectangular lifting surfaces
A method is presented for the calculation of lift coefficients for rectangular lifting surfaces of aspect ratios from 0.125 to 10 operating at finite depths beneath the water surface, including the zero depth or planing condition. Theoretical values are compared with experimental values obtained at various depths of submergence with lifting surfaces of aspect ratios from 0.125 to 10. The method can also be applied to hydrofoils with dihedral. Lift coefficients computed by this method are in good agreement with existing experimental data for aspect ratios from 0.125 to 10 and dihedral angles up to 10 degrees.
Date:
January 1958
Creator:
Wadlin, Kenneth L. & Christopher, Kenneth W.
System:
The UNT Digital Library
NACA Research on Slurry Fuels
"An extensive program was conducted to investigate the use of concentrated slurries of boron and magnesium in liquid hydrocarbon as fuels for afterburners and ramjet engines. Analytical calculations indicated that magnesium fuel would give greater thrust and that boron fuel would give greater range than are obtainable from jet hydrocarbon fuel alone. It was hoped that the use of these solid elements in slurry form would permit the improvement to be obtained without requiring unconventional fuel systems or combustors" (p. 1273).
Date:
1958
Creator:
Pinns, M. L.; Olson, W. T.; Barnett, H. C. & Breitwieser, R.
System:
The UNT Digital Library