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ABOUT BROWSE FEED
Regulated Power Supply
Technical drawing of electronic circuits and power supplies for use in nuclear reactors.
Reserves, Bed Characteristics, and Coking Properties of the Willow Creek Coal Bed, Kemmerer District, Lincoln County, Wyoming
Report issued by the Bureau of Mines discussing the coal reserves and coking properties of the Willow Creek bed in Lincoln County, Wyoming. Analyses of the coal bed are presented in detail. This report includes tables, illustrations, photographs, and a map.
Saw Tooth Generator and Discrinators
Technical drawing of signal generators for use in nuclear reactors.
Shear elastic properties of some high strength nonferrous metals as affected by plastic deformation and by heat treatment
No Description Available.
Studies of blade shank and pitch distribution for constant-speed propellers
No Description Available.
Study of the Alaska Tundra with Reference to its Reactions to Reindeer and other Grazing
The Alaska tundra varies in width from a few miles to 200 miles along the Bering Sea and from 100 to 150 miles along the Arctic coast. Plant composition is largely lichens, grasses, sedges, alpines, and shrubs, of which 16 distinct vegetative types are described in this report.
Suitability of ethers as aviation fuel components the knock-limited performance of several ethers blended with AN-F-28 fuel
No Description Available.
Summary of Airfoil Data
The historical development of NACA airfoils is briefly reviewed. New data are presented that permit the rapid calculation of the approximate pressure distributions for the older NACA four-digit and five-digit airfoils by the same methods used for the NACA 6-series airfoils. The general methods used to derive the basic thickness forms for NACA 6 and 7-series airfoils together with their corresponding pressure distributions are presented. Detail data necessary for the application of the airfoils to wing design are presented in supplementary figures placed at the end of the paper. The report includes an analysis of the lift, drag, pitching-moment, and critical-speed characteristics of the airfoils, together with a discussion of the effects of surface conditions. Available data on high-lift devices are presented. Problems associated with lateral-control devices, leading-edge air intakes, and interference are briefly discussed, together with aerodynamic problems of application. (author).
Summary of data relating to the effects of wing machine-gun and cannon installations on the aerodynamic characteristics of airplanes
No Description Available.
Summary of measurements in Langley full-scale tunnel of maximum lift coefficients and stalling characteristics of airplanes
The results of measurements in the Langley full-scale tunnel of the maximum lift coefficients and stalling characteristics of airplanes have been collected. The data have been analyzed to show the nature of the effects on maximum lift and stall of wing geometry, fuselages and nacelles, propeller slipstream, surface roughness, and wing leading-edge appendages such as ducts, armaments, tip slats, and airspeed heads. Comparisons of full-scale-tunnel and flight measurements of maximum lift and stall are included in some cases, and the effects of the different testing techniques on the maximum-lift measurements are also given.
A systematic investigation of pressure distributions at high speeds over five representative NACA low-drag and conventional airfoil sections
Pressure distributions determined from high-speed wind-tunnel tests are presented for five NACA airfoil sections representative of both low-drag and conventional types. Section characteristics of lift, drag, and quarter-chord pitching moment are presented along with the measured pressure distributions for the NACA 65sub2-215 (a=0.5), 66sub2-215 (a=0.6), 0015, 23015, and 4415 airfoils for Mach numbers up to approximately 0.85. A critical study is made of the airfoil pressure distributions in an attempt to formulate a set of general criteria for defining the character of high speed flows over typical airfoil shapes. Comparisons are made of the relative characteristics of the low-drag and conventional airfoils investigated insofar as they would influence the high-speed performance and the high-speed stability and control characteristics of airplanes employing these wing sections.
Tests on thin-walled celluloid cylinders to determine the interaction curves under combined bending, torsion, and compression or tension loads
No Description Available.
Tunnel-wall corrections to rolling and yawing moments due to aileron deflection in closed rectangular wind tunnels
No Description Available.
The two-dimensional incompressible potential flow over corrugated and distorted infinite surfaces
No Description Available.
United States Earthquakes, 1945
Report discussing earthquake activity in the United States during 1945. The report is broken down by regions and has sections for specific earthquakes.
Video Amplifier & Scope
Technical drawing of video amplifiers for nuclear reactors.
Wind-Tunnel Tests of a 1/5-Scale Semispan Model of the Republic XF-12 Horizontal Tail Surface
Wind-tunnel tests of a 1/5-scale semispan model of the Republic XF-12 horizontal tail surface equipped with an internally balanced elevator were conducted in the 6- by 6-foot test section of the Langley stability tunnel. The tests included measurements of the aerodynamic characteristics of the horizontal tail with and without a beveled trailing edge and also included measurements of the tab characteristics. The variation of the aerodynamic characteristics with boundary-layer conditions and leakage in the internal-balance chambers, measurements of the boundary-layer displacement thickness near the elevator hinge axis, and pressure distributions at the mean geometric chord were also obtained. The results showed that the hinge-moment characteristics of the elevator were critical to boundary-layer conditions and internal-balance leakage. Increasing the boundary-layer displacement thickness by use of roughness strips reduced the rate of change of elevator hinge moments with tab deflection by about 20 percent. The present horizontal tail appears to be unsatisfactory for longitudinal stability with power on, however, an increase in horizontal-tail lift effectiveness should correct this difficulty. The maneuvering stick force per unit acceleration will be extremely critical to minor variations of the elevator hinge moments if the elevator is linked directly to the stick.
Wind-Tunnel Tests of a 1/6-Scale Model of Republic XF-12 Vertical Tail Incorporating a De-Icing Air Duct
A 1/6-scale model of the Republic XF-12 vertical tail with stub fuselage, stub horizontal tail, and a de-icing air duct was tested in the Langley stability tunnel. The investigation consisted of a study of the effects of the duct, with and without air flow, on the aerodynamic characteristics of the model. The model tested was a revision of a model previously tested in the Langley stability tunnel. The revised model differed from the original model in that it incorporated a de-icing air duct, included a dorsal fin, and had a larger stub fuselage. A comparison of data obtained form tests of the original and revised models was made. The results of the investigation indicated that the air duct had very little effect on the aerodynamic characteristics of the model. A small change occurred in the variation of rudder hinge-moment coefficient with angle of attack but it is believed that this change can be corrected by a properly applied spring tab.
Wind-tunnel tests of a dual-rotating propeller having one component locked or windmilling
No Description Available.
Wind Tunnel Investigation of the Effects of Slot Shape and Flap Location on the Characteristics of a Low-Drag Airfoil Equipped with a 0.25-Chord Slotted Flap
Tests were conducted at dynamic pressure of 50 lb per square foot with lift drag and pitch moment measurements throughout useful angle of attack range for constant flap deflection and position of a low-drag airfoil. Two slots were investigated and practical flap paths were selected for each Slot shape had a negligible effect on the maximum lift coefficient flap deflected, the rounded-entry slot had lower profile drag.
Biological Action of Gamma and X-Rays
Report of experimentation on mice of exposure to daily doses of gamma radiation at two rates and the resultant damage.
Flight tests of the high-speed performance of a P-51B airplane (AAF no. 43-12105)
No Description Available.
High-speed wind-tunnel tests of semispan horizontal tails with fabric-covered and metal-covered elevators for a bomber airplane
No Description Available.
Power-off tests of the Northrop N9M-2 tailless airplane in the 40- by 80-foot wind tunnel
No Description Available.
Tests of a thermal ice-prevention system for a wing leading-edge landing-light installation
No Description Available.
Aerodynamic tests of a full-scale TBF-1 aileron installation in the Langley 16-foot high-speed tunnel
The failure of wing panels on a number of TBF-1 and TBM-1 airplanes in flight has prompted several investigations of the possible causes of failure. This report describes tests in the Langley 16-foot high-speed tunnel to determine whether these failures could be attributed to changes in the aerodynamic characteristics of the ailerons at high speeds. The tests were made of a 12-foot-span section including the tip and aileron of the right wing of a TBF-1 airplane. Hinge moments, control-link stresses due to aerodynamic buffeting, and fabric-deflection photographs were obtained at true airspeeds ranging from 110 to 365 miles per hour. The aileron hinge-moment coefficients were found to vary only slightly with airspeed in spite of the large fabric deflections that developed as the speed was increased. An analysis of these results indicated that the resultant hinge moment of the ailerons as installed in the airplane would tend to restore the ailerons to their neutral position for all the high-speed flight conditions covered in the tests. Serious aerodynamic buffeting occurred at up aileron angles of -10 degrees or greater because of stalling of the sharp projecting lip of the Frise aileron. The peak stresses set up in the aileron control linkages in the buffeting condition were as high as three times the mean stress. During the hinge-moment investigation, flutter of the test installation occurred at airspeeds of about 150 miles per hour. This flutter condition was investigated in some detail and slow-motion pictures were made of the motion of the wing tip and aileron. The flutter was found to involve simultaneous normal bending and chordwise oscillation of the wing and flapping of the aileron. The aileron motion appeared to be coupled with this flutter condition and was investigated in some detail and slow-motion pictures were made of the motion of the ...
Analysis and correlation of data obtained by six laboratories on fuel-vapor loss from fuel tanks during simulated flight
No Description Available.
Axial fatigue of 10 airplane wing-beam specimens by the resonance method
No Description Available.
Charts for the determination of wing torsional stiffness required for specified rolling characteristics or aileron reversal speed
No Description Available.
Charts showing stability and control characteristics of airplanes in flight
No Description Available.
Climb and high-speed tests of a Curtiss number 714-1C2-12 four-blade propeller on the Republic P-47C airplane
No Description Available.
The conformal transformation of an airfoil into a straight line and its application to the inverse problem of airfoil theory
A method of conformal transformation is developed that maps an airfoil into a straight line, the line being chosen as the extended chord line of the airfoil. The mapping is accomplished by operating directly with the airfoil ordinates. The absence of any preliminary transformation is found to shorten the work substantially over that of previous methods. Use is made of the superposition of solutions to obtain a rigorous counterpart of the approximate methods of thin-airfoils theory. The method is applied to the solution of the direct and inverse problems for arbitrary airfoils and pressure distributions. Numerical examples are given. Applications to more general types of regions, in particular to biplanes and to cascades of airfoils, are indicated. (author).
Development of detonation detector suitable for use in flight
No Description Available.
The effect of temperature on sheet metals for airplane firewalls
No Description Available.
Experimental constriction effects in high-speed wind tunnels
No Description Available.
Fatigue strength and related characteristics of aircraft joints I : comparison of spot-weld and rivet patterns in 24s-t alclad and 75s-t alclad
Report contains detailed results of a number of fatigue tests on spot-welded joints in aluminum alloys. The tests described include: (1) fatigue tests on spot-welded lap joints in sheets of unequal thickness of alclad 24s-t. These tests indicate that the fatigue strength of a spot-welded joint in sheets of two different gages is slightly higher than that of a similar joint in two sheets of the thinner gage but definitely lower than that of a similar joint in two sheets of the thicker gage. (2) Fatigue tests on spot-welded alclad 75s-t spot-welded lap-joint specimens of alclad 75s-t were not any stronger in fatigue than similar specimens of alclad 24s-t. (3) Fatigue tests on lap-joint specimens spot -welded after various surface preparations--these included ac welding wire-brushed surfaces, dc welding wire-brushed surfaces, and dc welding chemically cleaned surfaces. While the ac welds were strongest statically, the dc welds on wire-brushed surfaces were strongest in fatigue. Specimens prepared in this way were very nearly as strong as the best riveted specimens tested for comparison. (4) Fatigue tests on specimens spot-welded with varying voltage so as to include a wide range of static spot-weld strengths. The fatigue strengths were in the same order as the static strengths but showed less range. (author).
Flight and test-stand investigation of high-performance fuels in double-row radial air-cooled engines I : determination of cooling characteristics of flight engine
No Description Available.
Flight and test-stand investigation of high-performance fuels in double-row radial air-cooled engines II : flight knock data and comparison of fuel knock limits with engine cooling limits in flight
No Description Available.
Flight variables affecting fuel-vapor loss from a fuel tank
No Description Available.
Knock-limited performance of blends of AN-F-28 fuel containing 2 percent aromatic amines IV
No Description Available.
Knock-limited power outputs from a CFR engine using internal coolants I : monomethylamine and dimethylamine
No Description Available.
Material properties of two types of plastic-bonded glass cloth
No Description Available.
Measurement of flying qualities of a Douglas A-26B airplane (AAF No. 41-39120) I : longitudinal stability and control characteristics
No Description Available.
Performance of an exhaust-gas "blowdown" turbine on a nine-cylinder radial engine
No Description Available.
Performance of NACA eight-stage axial-flow compressor at simulated altitudes
No Description Available.
The relation between spanwise variations in the critical Mach number and spanwise load distributions
No Description Available.
Significance of alkylate-replacement values of aviation fuel components
No Description Available.
A Solution of the Direct and Inverse Potential Problems for Arbitrary Cascades of Airfoils
Methods are given of determining the potential flow plast an arbitrary cascade of airfoils and the inverse problem of determining an airfoil having a prescribed velocity distribution in cascade. Results indicated that Cartesian mapping function method may be satisfactorily extended to include cascades. Numerical calculation for computing cascades by Cartesian mapping function method is considerably greater than for single airfoils but much less than hitherto required for cascades. Detailed results are presented graphically.
Tests of Airfoils Designed to Delay the Compressibility Burble
No Description Available.
Flying qualities of a high-speed bomber with a dual pusher propeller aft of the empennage as estimated from wind-tunnel tests of a 1/8-scale powered model
No Description Available.