Technical Report Archive & Image Library (TRAIL) - 163 Matching Results

Search Results

Results: 1 - 50 next
The A.B.C. "Robin" (British): A Single-Seat Cabin Monoplane
Report discussing the A.B.C. Motors Robin, a single-seat monoplane that was built for pilot comfort, speed, and fuel efficiency. Information about the structural design, dimensions, weight, performance, and rough blueprints is included.
The A. B. Flygindustri "K 37" (Swedish Junkers): A Low-Wing All-Metal Military Airplane
Report discusses the characteristics of the K 37 all-metal long-wing monoplane and its use for long-distance scouting, as a day bomber, and as a heavy fighting airplane. Its engines, climbing capacity, action radius, bombing installation, fuselage, controls, and landing gear are explored in depth.
Aerodynamic theory and tests of strut forms 2
This report presents the second of two studies under the same title. In this part five theoretical struts are developed from distributed sources and sinks and constructed for pressure and resistance tests in a wind tunnel. The surface pressures for symmetrical inviscid flow are computed for each strut from theory and compared with those found by experiment. The theoretical and experimental pressures are found to agree quantitatively near the bow, only qualitatively over the suction range, the experimental suctions being uniformly a little low, and not at all near the stern.
Aeromechanical Experimentation (Wind Tunnel Tests)
The following report endeavors to show that aeromechanical experimentation has become an important aid to theory. Experiments can be tried with separate parts of airplanes or with models of whole airplanes, with propellers, and with anything else that comes into contact with moving air.
Airplane Drag
It has been less well understood that the induced drag (or, better said, the undesired increase in the induced drag as compared with the theoretical minimum calculated by Prandtl) plays a decisive role in the process of taking off and therefore in the requisite engine power. This paper seeks to clarify the induced drag.
Albessard "Triavion" Airplane (French): A Two-Seat Tandem Monoplane
Autostability is the watchword of this tandem monoplane. The tandem design causes a natural flat flight pattern and it can also land and take off from very short runways. Details of the form, wings, ailerons, fuselage, characteristics, performances, drawings, and photographs are provided.
The Amiot S.E.C.M. 110 C.1 : A Single-Seat Pursuit Monoplane
Circular presenting a description of the Amiot S.E.C.M. 110 C.1, which is a single-seat pursuit monoplane. Some of the design principles that the aircraft was built from are provided. A description of the design, components, dimensions, flight characteristics, and photographs are provided.
The Analysis of Aircraft Structures as Space Frameworks: Method Based on the Forces in the Longitudinal Members
The following examples do not take up the discussion of viewpoints to be heeded in determining the design of a framework for given external conditions. Rather they are methods for determining the forces in airplane fuselages and wings, though similar considerations are applied to certain simple cases of a different kind. The object of this treatise is to summarize and amplify these considerations from definite viewpoints.
Analysis of flight and wind-tunnel tests on Udet airplanes with reference to spinning characteristics
This report presents an analysis of results of wind-tunnel tests conducted at the D.V.L. Values were determined for the effectiveness of all the controls at various angles of attack. The autorotation was studied by subjecting the rotating model to an air blast.
Annual Report of the National Advisory Committee for Aeronautics (14th). Administrative Report Including Technical Reports Nos. 283 to 308
Report includes the National Advisory Committee for Aeronautics letter of submittal to the president, congressional report, summaries of the committee's activities and research accomplished, bibliographies, and financial report.
Autogenous Welding in Airplane Construction
Autogenous welding is discussed and various methods of testing those welds are presented.
The Balance of Moments and the Static Longitudinal Stability of Airplanes
A nomogram is developed which renders it possible by drawing a few lines, to determine: the location of the center of gravity for zero wing and tail moments; the longitudinal dihedral angle; the tail coefficient F(sub h) iota/F(sub t). Moreover there is no difficulty in determining the magnitude of the restoring moment or of the unstable moment.
Bauxite: Float-and-Sink Fractionations and Flotation Experiments
From Introduction: "This report presents the results of an investigation of the physical properties and characteristics of bauxite, with special reference to the possibility of applying commercial methods of concentration to low-grade bauxite."
The Bernard 20 C.1 (French): A Single-Seat Pursuit Monoplane
Circular presenting a description of the Bernard 20 C.1, which is made of wood and has four main parts: a one-piece wing with a fuselage in the middle, a rear section with the tail surfaces, an engine mount, and a landing gear.
Bibliography of Petroleum and Allied Substances, 1922 and 1923
From Introduction: "This bulletin is the seventh in this series of petroleum bibliographies published by the Bureau of Mines, Bulletins 149, 165, 180, 189, 216, and 220 being complications for the years 1915, 1916, 1917, 1918, 1919-20, and 1921, respectively. In this bulletin the same general plan of classification of references has been followed, but several additions have been made."
The Blackburn "Bluebird" Mark IV (British): All-Metal Biplane
Circular presenting a description of the Blackburn Bluebird Mark IV, which is an all-metal airplane. Details are provided regarding constructional features, the cockpit, the gasoline system, and the flight characteristics.
The Boulton and Paul "Partridge" (British): All-Metal Single-Seat Fighter
The Partridge is a tractor biplane of orthodox design. It has a single supercharged Jupiter VII engine.
The Bristol "Bulldog" (British): A Single-Seat All-Steel Fighter
Circular presenting a description of the Bristol Bulldog, which is a single-seat all-steel fighter aircraft powered by a Bristol Jupiter radial air-cooled engine. Details regarding the components, controls, stabilizers, design, flight characteristics, drawings, and photographs are provided.
Buckling Tests of Light-Metal Tubes
Report presenting an attempt to determine mathematically the buckling-strength curves of various centrally loaded light-metal tubes which exhibit conspicuous differences of behavior under compressive loads. For this purpose, Von Karman's method is used after adapting it to special conditions.
Calculation of the Pressures on Aircraft Engine Bearings
For aircraft engines the three principal operating conditions are idling speed, cruising speed, and diving with the engine stopped. In what follows, we will discuss a method which affords a good idea of the course of pressure for the above mentioned operating conditions. The pressures produced in the driving gear are of three kinds; namely, the pressure due to gases, the pressure due to the inertia of the rotating masses, and the pressure due to the inertia of the reciprocating masses.
The Canadian Gypsum Industry
From introduction: The production of gypsum is one of the oldest industries in Canada, and in point of gypsum output Canada ranks third among the countries of the world. Gypsum was discovered in the Maritime Provinces at a very early date, but there is no authentic record..of production until about 1822, when gypsum was mined on a small scale in Ontario. Since.then the production has grown slowly but steadily to more than a million tons. In 1928 the output was 1,205,846 short tons, valued at $3,622,007.
Cantilever Wings for Modern Aircraft: Some Aspects of Cantilever Wing Construction with Special Reference to Weight and Torsional Stiffness
In the foregoing remarks I have made an attempt to touch on some of the structural problems met with in cantilever wings, and dealt rather fully with a certain type of single-spar construction. The experimental test wing was a first attempt to demonstrate the principles of this departure from orthodox methods. The result was a wing both torsionally stiff and of light weight - lighter than a corresponding biplane construction.
Carburetion of Combustible Gas with Butane and Propane-Butane Mixtures with Particular Reference to the Carburetion of Water Gas
Report issued by the Bureau of Mines over the carburetion of many different fuels. The report pays particular attention to the carburetion of water gas. Carburetion methods and results are presented and discussed. This report includes tables, and illustrations.
Coal-Mine Ventilation Factors
Report discussing results from investigations of coal mining ventilation and discussing problems of ventilation in coal mining.
Coal-Washing Investigations: Methods and Tests
From Introduction: "The investigations described in this bulletin are confined to a study of the washing characteristics of bituminous coals. The washing characteristics of coals from many of the most important coal-producing fields of the Eastern and Central States were examined."
Condensed Data on the Aircraft Engines of the World
This compilation of the outstanding characteristics of the available aircraft engines of the world was prepared as a compact ready reference for desk use. It does not pretend to be anything but a skeleton outline of the characteristics of engines reported in the technical press as being in either the experimental, development, or production stage. At present progress is quite rapid and by the time this compilation is disseminated new models may have superseded those listed, or changes may have been made which will entirely change the characteristics given" (p. 1).
Contribution to the Aileron Theory
"In an attempt to treat theoretically the effect of ailerons, difficulty arises because an aileron may begin at any point of the wing. Hence the question arises as to how the transition of the lift distribution proceeds at such a point, since the effect of the aileron (i.e., the moment generated about the longitudinal axis) depends largely on this distribution. In order to answer this question regarding the lift distribution during irregular variations in the angle of attack at first independently of other influences, especially those of the wing tips, we have taken as the basis of the following theoretical discussion a wing of infinite span and constant chord which exhibits at one point an irregular variation in the angle of attack" (p. 1).
Contribution to the Technique of Landing Large Airships: Part 1
Many treatises in regard to construction of airship sheds are lacking in data on air currents, for which reason this phase of the problem will be here thoroughly discussed in connection with the accompanying photographs of currents.
Contribution to the Technique of Landing Large Airships: Part 2
Memorandum presenting a description of the development of the mooring mast and how it contributes to the technique of landing large airships. Some of its fundamental requirements and how it can factor into safe landings are provided.
Correcting Engine Tests for Humidity
Note presenting tests using a multicylinder engine to determine the effect that atmospheric humidity has on some phases of engine performance. Three test series with different types of fuel were carried out. The results indicate that failure to allow for the effect of differences in atmospheric humidity may introduce errors as great as would be occasioned by failure to allow for changes in barometric pressure.
Corrosion Embrittlement of Duralumin. V: Results of Weather-Exposure Tests
In a series of weather exposure tests of sheet duralumin, upon which accelerated corrosion tests in the laboratory by the wet-and-dry corrosion method in a sodium chloride solution has already been carried out, a close parallelism between the results of the two kinds of tests was found to exist. The exposure tests showed that the lack of permanence of sheet duralumin is largely, if not entirely, due to corrosion. A corrosion attack of an intercrystalline nature is very largely responsible for the degree of embrittlement produced.
Corrosion Embrittlement of Duralumin. VI: The Effect of Corrosion Accompanied by Stress on the Tensile Properties of Sheet Duralumin
The effect of corrosion on the tensile properties of duralumin while stressed is shown in graphical form. According to the test results, duralumin sheet, coated with aluminum, maintains its initial properties unimpaired for corrosion periods as long as 60 days with an applied tensile stress as high as 20,000 lb/sq.in., which is approximately one-half the stress corresponding to the yield point as defined here. In these tests, that material which had been heat-treated by being quenched in cold water, though far inferior to similar material having the aluminum coating, was superior to the sheet material which was heat treated by being quenched in hot water.
Crank Case Scavenging of Two-Stroke-Cycle Engines
This report presents the results of tests on two-stroke-cycle Diesel engines to determine the efficiency of the crank case scavenging pump. It was determined that efficiencies were between 95 and 100%.
Curves Showing Column Strength of Steel and Duralumin Tubing
Given here are a set of column strength curves that are intended to simplify the method of determining the size of struts in an airplane structure when the load in the member is known. The curves will also simplify the checking of the strength of a strut if the size and length are known. With these curves, no computations are necessary, as in the case of the old-fashioned method of strut design. The process is so simple that draftsmen or others who are not entirely familiar with mechanics can check the strength of a strut without much danger of error.
Danger of Ice Formation on Airplanes
This paper relates the different types of ice formations that can occur on airplanes and the dangers that they pose.
The De Havilland D.H. 75 "Hawk Moth" (British): Cabin Monoplane
The Hawk Moth is designed as a passenger aircraft with comfort in mind. It seats 4. The tail is of metal construction, while the wings are of wood. It has a total loaded weight of 3500 lbs.
The Design of Plywood Webs for Airplane Wing Beams
This report deals with the design of plywood webs for wooden box beams to obtain maximum strength per unit weight. A method of arriving at the most efficient and economical web thickness, and hence the most suitable unit shear stress, is presented and working stresses in shear for various types of webs and species of plywood are given. The questions of diaphragm spacing and required glue area between the webs and flange are also discussed.
Device for the Automatic Control of Airplanes
This report provides a description of an automatic control mechanism that consists of an automatic elevator control, aileron control, and a rudder control. Each automatic control can be independently switched on or off.
The Drag and Interference of a Nacelle in the Presence of a Wing
A wing interference investigation was conducted to determine why the N.A.C.A. cowling did not yield the expected increase in speed when adapted to the outboard nacelles of trimotored airplanes. The results indicate that the drag and interference of the engine nacelle with the cowling, when combined with a thick wing, can be reduced from its value as originally applied by changing its position and fairing it into the wing.
Drilling and Blasting in Metal-Mine Drifts and Crosscuts
From Introduction: "This report shows the results obtained and conclusions drawn from observing the blasting of 108 rounds at 13 mines in six different States. Kinds of rock drills, drill steel, and forms of drill bits are not considered."
The effect of a flap and ailerons on the N.A.C.A. M-6 airfoil section
"This report contains the results obtained at the Langley Memorial Aeronautical Laboratory on an N. A. C. A. M-6 airfoil, fitted with a flap and ailerons, and tested in the variable density wind tunnel at a density of 20 atmospheres. Airfoil characteristics are given for the model up to 48 degree angle of attack with the flap set at various angles, and also with the ailerons set at similar angles. The approximate lift distribution and the center of pressure variation along the span are determined with the model at 18 degree angle of attack and with the ailerons displaced at 20 degrees" (p. 1).
The effect of cowling on cylinder temperatures and performance of a Wright J-5 engine
This report presents the results of tests conducted to determine the effect of different amounts and kinds of cowling on the performance and cylinder temperatures of a standard Wright J-5 engine. These tests were conducted in conjunction with drag and propeller tests in which the same cowlings were used. Four different cowlings were investigated varying from the one extreme of no cowling on the engine to the other extreme of the engine completely cowled and the cooling air flowing inside the cowling through an opening in the nose and out through an annular opening at the rear of the engine. Each cowling was tested at air speeds of approximately 60, 80, and 100 miles per hour.
The Effect of Fuel Consumption on Cylinder Temperatures and Performance of a Cowled Wright J-5 Engine
Given here are the results of tests made to determine the effect of fuel consumption on the cylinder temperatures and the performance of a cowled Wright J-5 engine. The results of these tests indicate that enriching the mixture by increasing the carburetor size results in a reduction in cylinder head and barrel temperatures. The cylinders shielded by the magnetos or the points on the cylinder that do not receive a free flow of cooling air increase most rapidly in temperature as the mixture is leaned.
Effect of Intake Pipe on the Volumetric Efficiency of an Internal Combustion Engine
" The writer discusses the phenomena of expansion and compression which alternately take place in the cylinders of four-stroke engines during the induction process at a high mean piston speed due to the inertia and elasticity of the mixture in the intake pipe. The present paper is intended to demonstrate theoretically the existence of a most favorable pipe length for charging" (p. 1).
Effect of Oxygen on the Ignition of Liquid Fuels
The ignition temperature, ignition lag, and ignition strength of simple and homogeneous fuels in combustion air of small oxygen content differ from what they are in air of greater oxygen content. In the case of small oxygen content, these fuels behave as if mixed unevenly. In the case of air with a definite oxygen content, the simple fuels have two ignition points, between which ignition takes place within a certain temperature range. The phenomena are explained by pyrogenous decomposition, comparison of the individual heat quantities, and the effect of the walls.
The Effect of Reduction Gearing on Propeller-Body Interference as Shown by Full-Scale Wind-Tunnel Tests
This report presents the results of full-scale tests made on a 10-foot 5-inch propeller on a geared J-5 engine and also on a similar 8-foot 11-inch propeller on a direct-drive J-5 engine. Each propeller was tested at two different pitch settings, and with a large and a small fuselage. The investigation was made in such a manner that the propeller-body interference factors were isolated, and it was found that, considering this interference only, the geared propellers had an appreciable advantage in propulsive efficiency, partially due to the larger diameter of the propellers with respect to the bodies, and partially because the geared propellers were located farther ahead of the engines and bodies.
Effect of Stressed Covering on Strength of Internal Girders of a Wing
In practice the actual maximum stress is greater than the stress determined by the simple girder theory, which overestimates the bearing or supporting capacity of the flange. The fact is that the assumptions of the simple girder theory no longer hold true, since normal transverse and shearing stresses are engendered in the plane of the flange.
The Effect of Supercharger Capacity on Engine and Airplane Performance
This report presents the results of an investigation to determine the effect of different supercharger capacities on the performance of an airplane and its engine . The tests were conducted on a DH4-M2 airplane powered with a Liberty 12 engine. In this investigation four supercharger capacities, obtained by driving a roots type supercharger at 1.615, 1.957, 2.4, and 3 time engine speed, were used to maintain sea-level pressure at the carburetor to altitudes of 7,000, 11,500, 17,000, and 22,000 feet, respectively. The performance of the airplane in climb and in level flight was determined for each of the four supercharger drive ratios and for the unsupercharged condition.
The effect of the wings of single engine airplanes on propulsive efficiency as shown by full scale wind tunnel tests
An investigation was conducted to determine the effect of the wings on propulsive efficiency. The wings are shown to cause a reduction of 1 percent to 3 percent in propulsive efficiency, which is about the same for monoplane as well as biplane wings.
Effect of turbulence in wind-tunnel measurements
This paper gives some quantitative measurements of wind tunnel turbulence and its effect on the air resistance of spheres and airship models, measurements made possible by the hot wire anemometer and associated apparatus in its original form was described in Technical Report no. 320 and some modifications are presented in an appendix to the present paper. One important result of the investigation is a curve by means of which measurements of the air resistance of spheres can be interpreted to give the turbulence quantitatively. Another is the definite proof that the discrepancies in the results on the N. P. L. Standard airship models are due mainly to differences in the turbulences of the wind tunnels in which the tests were made.
Back to Top of Screen