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Effect of reducing valve overlap on engine and compound-power-plant performance
Report presenting an experimental investigation of a 62 degree valve overlap, 18-cylinder, air-cooled, radial engine modified with 40 degree-valve-overlap cams to determine the effect of a change in valve overlap on engine performance. Computations were made to show the effect of change in valve overlap on compound-engine performance.
Date:
June 1948
Creator:
Boman, David S. & Kaufman, Samuel J.
System:
The UNT Digital Library
The effect of simulated icing on propeller performance
Testing of a 10-foot-diameter three-blade Curtiss 89301-15 propeller with Clark Y blade sections was conducted in the 16-foot high-speed tunnel to determine the effect of simulated ice on the aerodynamic characteristics of the propeller. The propellers were tested on a 2000-horsepower dynamometer at rotational speed 1800 rpm at several blade angles and airspeeds. Results regarding the effect of icing and constant-power propeller operation are provided.
Date:
June 1946
Creator:
Corson, Blake W., Jr. & Maynard, Julian D.
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
Effect of steady rolling on longitudinal and directional stability
Report presenting a theoretical investigation of the effects of steady rolling on the longitudinal and directional stability of aircraft. Simplifying assumptions have been made with regard to the longitudinal and lateral motions of the airplane in order to obtain a solution which shows the principal effects of rolling motion.
Date:
June 1948
Creator:
Phillips, William H.
System:
The UNT Digital Library
Effect of Temperatures From -70 to 600 Degrees Fahrenheit on Strength of Adhesive-Bonded Lap Shear Specimens of Clad 24S-T3 Aluminum Alloy and of Cotton-and Glass-Fabric Plastic Laminates
Report presenting an evaluation of the performance of 14 commercial adhesives at a range of temperatures in lap shear specimens of clad 24S-T aluminum alloy to itself and that of 7 commercial adhesives at a range of temperatures in lap joints of cotton-fabric-phenolic laminate to itself, of glass-fabric-polyester laminate to itself, and in joints of each of these laminates to clad aluminum. Results regarding aluminum to aluminum joints and plastic to plastic and plastic to aluminum joints are provided.
Date:
June 1952
Creator:
Eickner, H. W.; Olson, W. Z. & Blomquist, R. F.
System:
The UNT Digital Library
Effect of the proximity of the wing first-bending frequency and the short-period frequency on the airplane dynamic-response factor
Report presenting a study of the effect of the frequency of the lowest wing structural mode on the airplane center-of-gravity dynamic-response factor was made my employing simplified transfer functions.
Date:
June 1958
Creator:
Huss, Carl R. & Donegan, James J.
System:
The UNT Digital Library
Effect of trailing-edge thickness on lift at supersonic velocities
Report presenting measurements of lift made on various rectangular-plan-form wings differing in trailing-edge thickness, profile shape, maximum thickness ratio, and aspect ratio. Experiments were conducted at a range of Mach numbers, Reynolds numbers, and wings with and without boundary-layer trips. Results regarding a comparison of experimental results with theory at moderate supersonic Mach numbers and calculations for hypersonic Mach numbers are provided.
Date:
June 1955
Creator:
Chapman, Dean R. & Kester, Robert H.
System:
The UNT Digital Library
Effect of Transient Heating on Vibration Frequencies of Some Simple Wing Structures
"Thermal stresses, which may result from transient heating, can cause changes in the effective stiffness of wing structures. Some effects of this change in stiffness were investigated experimentally by radiantly heating three types of simple wing structures: a uniform plate, a solid double-wedge section, and a circular-arc multiweb-wing section. Changes in stiffness were determined by measuring the changes in natural frequency of vibration during transient heating. Some comparisons are made between theoretical calculations and the measured data" (p. 1).
Date:
June 1957
Creator:
Vosteen, Louis F.; McWithey, Robert R. & Thomson, Robert G.
System:
The UNT Digital Library
Effect of Variation in Rivet Strength on the Average Stress at Maximum Load for Aluminum-Alloy, Flat, Z-Stiffened Compression Panels That Fail by Local Buckling
"A study is made of the effect of variation in rivet strength on the average panel stress at maximum load for 75S-T6 aluminum-alloy, flat, Z-stiffened compression panels that fail by local buckling. A curve is presented for the determination of the relationship between strength, diameter, and pitch of the rivets, and the strength of stiffened, flat compression panels of such proportions that failure is by local buckling" (p. 1).
Date:
June 1953
Creator:
Dow, Norris F.; Hickman, William A. & Rosen, B. Walter
System:
The UNT Digital Library
Effectiveness of Ceramic Coatings in Reducing Corrosion of Five Heat-Resistant Alloys by Lead-Bromide Vapors
Note presenting testing to determine whether lead compounds in the combustion products of high-octane fuel are a contributing factor in causing failures of the heat-resistant alloy parts in aircraft exhaust systems. To obtain answers for five heat-resistant alloys, a test was devised in which the alloy specimens in an uncoated condition, in a preoxidized condition, and with three different ceramic coatings were exposed for 6 hours to lead-containing vapors in an air atmosphere at 3 different temperatures.
Date:
June 1951
Creator:
Moore, Dwight G. & Mason, Mary A.
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
Effects of Horizontal-Tail Position and a Wing Leading-Edge Modification Consisting of a Full-Span Flap and a Partial-Span Chord-Extension on the Aerodynamic Characteristics in Pitch at High Subsonic Speeds of a Model With a 45 Degree Sweptback Wing
Note presenting an investigation conducted in the high-speed 7- by 10-foot tunnel to determine the effects of varying the horizontal-tail position relative to the wing chord plane on the aerodynamic characteristics in pitch of a general research model having a 45 degree sweptback wing of aspect ratio 4, taper ratio 0.30, and NACA 65A006 airfoil sections. The investigation also included the effects of a wing modification consisting of a full-span leading-edge flap deflected 6 degrees and an outboard partial-span chord-extension.
Date:
June 1957
Creator:
Morrison, William D., Jr. & Alford, William J., Jr.
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
Effects of Range of Stress and of Special Notches on Fatigue Properties of Aluminum Alloys Suitable for Airplane Propellers
"Laboratory tests were made to obtain information on the load-resisting properties of X76S-T aluminum alloy when subjected to static, impact, and repeated loads. Results are presented from static-load test of unnotched specimens in tension and in torsion and of notched specimens in tension. Charpy impact values obtained from bend tests on notched specimens and tension impact values for both notched and unnotched specimens tested at several different temperatures are included" (p. 1).
Date:
June 1942
Creator:
Dolan, Thomas J.
System:
The UNT Digital Library
Effects of Rapid Heating on Strength of Airframe Components
Note presenting results of several experimental investigations which indicate the effects of rapid heating on the bending strength of multiweb beams and ring-stiffened cylinders. Thermal stresses are shown to reduce the bending load carried at buckling by both beams and cylinders.
Date:
June 1957
Creator:
Pride, Richard A.; Hall, John B., Jr. & Anderson, Melvin S.
System:
The UNT Digital Library
Effects of Some Present-Day Airplane Design Trends on Requirements for Lateral Stability
Note presenting computations made to determine the effects of some airplane design trends on the fin area and the dihedral angle required for lateral stability. The specific factors studied were wing loading, moments of inertia in roll and yaw, wing chord, and tail length. The results of the computations are presented in the form of diagrams of variations of fin area with dihedral angle for neutral stability.
Date:
June 1941
Creator:
Bamber, Millard J.
System:
The UNT Digital Library
Effects of temperature distribution and elastic properties of materials on gas-turbine-disk stresses
Report presenting calculations to determine the influence of changes in temperature distribution and elastic material properties on calculated elastic stresses for a typical gas-turbine disk. Severe temperature gradients caused thermal stresses of sufficient magnitude to reduce the operating safety of the disk.
Date:
June 1947
Creator:
Holms, Arthur G. & Faldetta, Richard D.
System:
The UNT Digital Library
Elastic Buckling of a Simply Supported Plate Under a Compressive Stress That Varies Linearly in the Direction of Loading
"Results are presented of calculations for the elastic buckling load of a simply supported flat rectangular plate of uniform thickness subjected to unequal compressive stresses at two opposite edges, with a linear variation of stress between the two edges. The difference between the compressive stresses at the two loaded edges is equilibrated by shear stresses along the other two edges. The results show that a plate with a linear stress gradient will buckle at an average stress that is lower, but at a maximum stress that may be appreciably higher, than the uniform compressive buckling stress of the same plate" (p. 1).
Date:
June 1949
Creator:
Libove, Charles; Ferdman, Saul & Reusch, John J.
System:
The UNT Digital Library
An Empirical Equation for the Coefficient of Heat Transfer to a Flat Surface From a Plane Heated-Air Jet Directed Tangentially to the Surface
Note presenting an investigation of the heat transfer to a surface from plane heated-air jets discharged tangentially to the surface to provide heat-transfer relationships required in the design of heated-air jet installations for aircraft windshield fog prevention. Experimental temperature, velocity, and heat-transfer data were obtained by tests in which the initial jet temperature and velocity were varied.
Date:
June 1946
Creator:
Zerbe, John & Selna, James
System:
The UNT Digital Library
An Empirical Equation for the Coefficient of Heat Transfer to a Flat Surface From a Plane Heated-Air Jet Directed Tangentially to the Surface
Note presenting an investigation of the heat transfer to a surface from plane heated-air jets discharged tangentially to the surface was conducted to provide heat-transfer relationships required in the design of heated-air jet installations for aircraft windshield fog prevention. Experimental temperature, velocity, and heat-transfer data were obtained by tests in which the initial jet temperature and velocity were varied.
Date:
June 1946
Creator:
Zerbe, John & Selna, James
System:
The UNT Digital Library
Empirical Method for Frequency Compensation of the Hot-Wire Anemometer
Note presenting a description of the improvements in the design of equipment associated with the hot-wire anemometer for the measurement of fluctuating-air flow quantities. An improved technique and an electronic circuit for the frequency compensation of a hot wire are presented.
Date:
June 1947
Creator:
Runyan, Raymond A. & Jeffries, Robert J.
System:
The UNT Digital Library
Endurance and Other Properties at Low Temperatures of Some Alloys for Aircraft Use
"The low temperature endurance properties of materials for aircraft construction are not well known. In order to determine them, apparatus for testing endurance at -40 C has been devised. The endurance properties of monel metal, low-carbon stainless steel, "18 and *, " 3 1/2% Ni steel and chromium-molybdenum steel have been determined at -40 C and at room temperature about +20 C. Tensile, impact and hardness tests of these materials have also been made at various temperatures" (p. 1).
Date:
June 1931
Creator:
Russell, H. W. & Welcker, W. A., Jr.
System:
The UNT Digital Library
Estimation of Compressible Boundary-Layer Growth Over Insulated Surfaces With Pressure Gradient
Note presenting the incompressible boundary-layer theory of Truckenbrodt extended using a modified Stewartson-type transformation to include compressible boundary-layer development over insulated surfaces. The method is applicable to two-dimensional and axisymmetric, laminar and turbulent boundary layer, and accounts for the pressure gradient along the wall for both compressible and incompressible flow. Some experimental measurements of the boundary layer on small axisymmetric bodies on the wall of a supersonic wind tunnel compared with theoretical predictions.
Date:
June 1957
Creator:
Englert, Gerald W.
System:
The UNT Digital Library
Estimation of control forces of spring-tab ailerons from wind-tunnel data
Report presenting a method for estimating the control forces of spring-tab ailerons from nonlinear wind-tunnel data. Two principal arrangements of the ailerons and spring unit were used, one with the ailerons interconnected and a central spring unit and an arrangement with no interconnection between the ailerons with individual preloaded spring units for each aileron.
Date:
June 1947
Creator:
Deters, Owen J.
System:
The UNT Digital Library