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Partner:
UNT Libraries Government Documents Department
Decade:
1920-1929
Collection:
National Advisory Committee for Aeronautics Collection
- Some effects of air flow on the penetration and distribution of oil sprays
- Tests were made to determine the effects of air flow on the characteristics of fuel sprays from fuel injection valves. Curves and photographs are presented showing the airflow throughout the chamber and the effects of the air flow on the fuel spray characteristics. It was found that the moving air had little effect on the spray penetration except with the 0.006 inch orifice. The moving air did, however, affect the oil particles on the outside of the spray cone. After spray cut-off, the air flow rapidly distributed the atomized fuel throughout the spray chamber. digital.library.unt.edu/ark:/67531/metadc54013/
- Wind tunnel pressure distribution tests on a series of biplane wing models Part III : effects of charges in various combinations of stagger, gap, sweepback, and decalage
- A concept for the calculation of the vortex lift of sharp-edge delta wings is presented and compared with experimental data. The concept is based on an analogy between the vortex lift and the leading-edge suction associated with the potential flow about the leading edge. This concept, when combined with potential-flow theory modified to include the nonlinearities associated with the exact boundary condition and the loss of the lift component of the leading-edge suction, provides excellent prediction of the total lift for a wide range of delta wings up to angles of attack of 20 degrees or greater. digital.library.unt.edu/ark:/67531/metadc54019/
- 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. digital.library.unt.edu/ark:/67531/metadc65392/
- 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. A free flow of air past the cylinders is essential for satisfactory operation on a lean mixture. The results of these tests show that the Wright J-5 engine can withstand severe temperatures for short periods of operation. The test results also show to what extent destructive temperatures may be avoided by enriching the mixture. digital.library.unt.edu/ark:/67531/metadc54007/
- Some studies on the aerodynamic effect of the gap between airplane wings and fuselages
- The general result indicated by this study is that if desirable from any viewpoint the gap between wing and fuselage may be closed without detrimental aerodynamic effects, and with a given monoplane there is less drag if the wing is directly on top of the fuselage than if it is parasol. digital.library.unt.edu/ark:/67531/metadc54003/
- Technical details in the structural development of Rohrbach seaplanes
- The recent trial flights and acceptance tests of the Rohrbach "Romar," the largest seaplane in the world, have yielded results fully confirming the principles followed in its development. Its take-off weight of 19,000 kg, its beating the world record for raising the greatest useful load to 2000 m by almost 2500 kg and its remarkable showing in the seaworthiness tests are the results of intelligent researches, the guiding principles of which are briefly set forth in this article. digital.library.unt.edu/ark:/67531/metadc65393/
- The A. B. Flygindustri "K 37" (Swedish Junkers) : A Low-Wing All-Metal Military Airplane
- No Description digital.library.unt.edu/ark:/67531/metadc64629/
- The Bristol "Bulldog" (British): A Single-Seat All-Steel Fighter
- No Description digital.library.unt.edu/ark:/67531/metadc64623/
- 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. digital.library.unt.edu/ark:/67531/metadc54061/
- 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. digital.library.unt.edu/ark:/67531/metadc54064/
- Experiments with a wing model from which the boundary is removed by suction
- The present report deals with a series of tests made for the purpose of improving flow conditions about wings by applying the suction principle (increase of the lift coefficient and reduction of the drag about very thick wing sections). Though not conclusive, the report contains interesting results. digital.library.unt.edu/ark:/67531/metadc65387/
- The impact on seaplane floats during landing
- In order to make a stress analysis of seaplane floats, and especially of the members connecting the floats with the fuselage, it is of great importance to determine the maximum pressure acting on the floats during landing. Here, the author gives a formula for maximum pressures during landing that permits one to apply experimental results to different bodies and different velocities. The author notes that the formula checks very well with experimental results. digital.library.unt.edu/ark:/67531/metadc54062/
- Wind tunnel pressure distribution tests on a series of biplane wing models Part II : effects of changes in decalage, dihedral, sweepback and overhang
- This preliminary report furnishes information on the changes in the forces on each wing of a biplane cellule when the decalage, dihedral, sweepback and overhang are separately varied. The data were obtained from pressure distribution tests made in the Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory. Since each test was carried up to 90 degree angle of attack, the results may be used in the study of stalled flight and of spinning and in the structural design of biplane wings. digital.library.unt.edu/ark:/67531/metadc53992/
- Wind tunnel pressure distribution tests on an airfoil with trailing edge flap
- This report deals with pressure distribution tests on an airfoil with a conventional trailing edge flap. These tests were conducted in the Atmospheric Wind Tunnel of the National Advisory Committee for Aeronautics. Maximum chord loadings were obtained with the flap displaced downward and with the airfoil at large angles of attack. Greater changes were produced in the normal force and in the center of pressure travel by up-flap than by an equal down-flap displacement. digital.library.unt.edu/ark:/67531/metadc53999/
- Wind tunnel tests on airfoil boundary control using a backward opening slot
- This report presents the results of an investigation to determine the effect of boundary layer control on the lift and drag of an airfoil equipped with a backward opening slot. Various slot locations, widths of opening, and pressures, were used. The tests were conducted in the Five-Foot Atmospheric Wind Tunnel of the Langley Memorial Aeronautical Laboratory. The greatest increase in maximum lift was 96 per cent, the greatest decrease in minimum drag was 27 per cent, and the greatest increase in the ratio, maximum lift coefficient/minimum drag coefficient, was 151 per cent. digital.library.unt.edu/ark:/67531/metadc53977/
- Wind tunnel tests on an airfoil equipped with a split flap and a slot
- The investigation described in this report is concerned with the changes in the aerodynamic characteristics of an airfoil which are produced by a gauze-covered suction slot, located near the leading edge, and connected by an air passage to a split flap at the trailing edge. The tests were conducted at the Langley Memorial Aeronautical Laboratory. At the larger values of lift coefficient where the action of the slot might be expected to be most effective, the pressure differences were such that the air flowed out of the slot rather than in through it, and in consequence, the maximum lift coefficient was decreased. digital.library.unt.edu/ark:/67531/metadc53979/
- The A.B.C. "Robin" (British) : a single-seat cabin monoplane
- No Description digital.library.unt.edu/ark:/67531/metadc64615/
- The Fairey III.F (British): a General Purpose Biplane
- No Description digital.library.unt.edu/ark:/67531/metadc64429/
- Full scale investigation of the drag of a wing radiator
- Tests were made on the 1927 Williams racer in order to determine the effect of the wing radiator on the airfoil characteristics. It was found that the radiator doubled the minimum drag of the portion of the wing it covered, and also reduced the lift somewhat. digital.library.unt.edu/ark:/67531/metadc54046/
- Metal construction development. Part IV : moments of inertia of thin corrugated sections
- No Description digital.library.unt.edu/ark:/67531/metadc65382/
- Some experiments on autorotation of an airfoil
- These experiments show that the rate of auto rotation of a monoplane airfoil is reduced by sweepback, ceasing entirely when the sweepback is 30 degrees. In addition a very serious increase in rate and range of auto rotation with yaw is shown. digital.library.unt.edu/ark:/67531/metadc54056/
- Tests of four racing type airfoils in the twenty-foot propeller research tunnel
- Tests were made on four racing type airfoils in order to determine the high speed characteristics of the wings. digital.library.unt.edu/ark:/67531/metadc54041/
- Viscosity of diesel engine fuel oil under pressure
- In the development of Diesel engine fuel injection systems it is necessary to have an approximate knowledge of the absolute viscosity of the fuel oil under high hydrostatic pressures. This report presents the results of experimental tests conducted by Mr. Jackson Newton Shore, utilizing the A.S.M.E. high pressure equipment. digital.library.unt.edu/ark:/67531/metadc54033/
- Welding of stainless materials
- It would appear that welds in some stainless steels, heat-treated in some practicable way, will probably be found to have all the resistance to corrosion that is required for aircraft. Certainly these structures are not subjected to the severe conditions that are found in chemical plants. digital.library.unt.edu/ark:/67531/metadc65385/
- Welding rustproof steels
- The following experimental results will perhaps increase the knowledge of the process of welding rustproof steels. The experiments were made with two chrome-steel sheets and with two chrome-steel-nickel sheets having the composition shown in Table I. digital.library.unt.edu/ark:/67531/metadc65384/
- Wind tunnel tests on a model of a monoplane wing with floating ailerons
- This report describes preliminary wind tunnel tests on a model of a monoplane wing equipped with wing tip floating ailerons. Lift and drag, as well as rolling and yawing moments, were measured. digital.library.unt.edu/ark:/67531/metadc54036/
- The formation of ice upon airplanes in flight
- This report describes the atmospheric conditions under which ice is formed upon the exposed parts of airplanes in flight. It identifies the formation found under different conditions, and describes some studies of preventative means. digital.library.unt.edu/ark:/67531/metadc54023/
- The "K 47" of the A.B. Flygindustri : An Armored Pursuit Monoplane
- No Description digital.library.unt.edu/ark:/67531/metadc65137/
- Metal construction development. Part II : strip metal construction - wing spars
- No Description digital.library.unt.edu/ark:/67531/metadc65378/
- Metal construction development. Part III : strip metal construction - wing ribs
- Strip metal construction of wing spars are presented as well as workshop practices. digital.library.unt.edu/ark:/67531/metadc65381/
- The Parnall "Pipit" (British) : A Single-Seat Ship's Fighter
- The Parnall Pipit is a single-seat ships fighter equipped with a Rolls Royce "F" type engine and armed with two synchronized Vickers guns. It can also be configured to carry bombs under the wings. digital.library.unt.edu/ark:/67531/metadc65136/
- Sphere drag tests in the variable density wind tunnel
- The air forces on a twenty-centimeter sphere were measured after it had been rebuilt as an open throat type. The results from tests made at widely different densities and airspeeds and also on a smaller sphere are given. digital.library.unt.edu/ark:/67531/metadc54020/
- Spiral tendency in blind flying
- The flight path followed by an airplane which was being flown by a blindfolded pilot was observed and recorded. When the pilot attempted to make a straight-away flight there was a tendency to deviate from the straight path and to take up a spiral one. digital.library.unt.edu/ark:/67531/metadc54031/
- 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. digital.library.unt.edu/ark:/67531/metadc65376/
- Torsional rigidity of cantilever wings with constant spar and rib sections
- The present paper treats less of the effect of the union (of spars and ribs, namely, the reduction of the bending moment at the fixed ends of the spars) than of its influence on the torsional rigidity of the wing. The calculations are carried out for a two-spar wing of constant cross section, in which the ribs are replaced by a continuous member of constant rigidity. digital.library.unt.edu/ark:/67531/metadc65368/
- The use of wheel brakes on airplanes
- The results of tests to determine the effect of wheel brakes on the landing run of an airplane under conditions of load and at various wind velocities are presented. digital.library.unt.edu/ark:/67531/metadc54015/
- Wind tunnel pressure distribution tests on a series of biplane wing models
- This report is on the changes in forces on each wing of a biplane cellule when either the stagger or the gap is varied. Since each test was carried up to a 90 degree angle of attack, the results may be used in the study of stalled flight and of spinning as well as in the structural design of biplane wings. digital.library.unt.edu/ark:/67531/metadc54010/
- Wings with nozzle-shaped slots
- Even before the publication of the results of the Gottingen experiments on the removal of the boundary layer by suction, experiments with nozzle-slotted wings were begun. A report of those experiments will be given here. Taken collectively, the experiments show that, as regards increasing the lift values, the effect of the air flowing from the nozzle-shaped slots is similar to the effect produced in the case of ordinary slotted wings. The high lift values are attained, however, at the smaller angles of attack employed in ordinary flight. digital.library.unt.edu/ark:/67531/metadc65371/
- Correcting engine tests for humidity
- No Description digital.library.unt.edu/ark:/67531/metadc54005/
- Investigation of atomization in carburetors
- This report presents methods by which it is possible to determine, in a simple manner, both pressure atomization and carburetor atomization. digital.library.unt.edu/ark:/67531/metadc65365/
- Investigation of the Effect of the Fuselage on the Wing of a Low-Wing Monoplane
- No Description digital.library.unt.edu/ark:/67531/metadc65361/
- Pressure distribution on a slotted R.A.F. 31 airfoil in the variable density wind tunnel
- Measurements were made in the variable density wind tunnel to determine the pressure distribution over one section of a R.A.F. 31 airfoil with a leading edge slot fully open. To provide data for the study of scale effect on this type of airfoil, the tests were conducted with air densities of approximately one and twenty atmospheres. digital.library.unt.edu/ark:/67531/metadc54001/
- Strength of tubing under combined axial and transverse loading
- No Description digital.library.unt.edu/ark:/67531/metadc53994/
- 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. These results are in excellent agreement with the results of previous laboratory and exposure tests. digital.library.unt.edu/ark:/67531/metadc53988/
- 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. digital.library.unt.edu/ark:/67531/metadc53990/
- Materials and methods of construction in light structures
- Different methods of constructing light airplanes are presented with a view toward increasing production and efficiency. digital.library.unt.edu/ark:/67531/metadc65364/
- On the Strength of Box Type Fuselages
- The present investigation relates to a box-type fuselage with sides consisting of thin smooth sheet metal, stiffened by longitudinal members riveted to the flanged channel-section bulkheads or transverse frames and to the semicircular corrugated corner stiffenings. The results obtained in this particular case can be applied to a great number of similar structures. digital.library.unt.edu/ark:/67531/metadc65363/
- 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. digital.library.unt.edu/ark:/67531/metadc53981/
- Landing and braking of airplanes
- In the numerical examples, we have considered an airplane landing in calm air in a fixed direction after crossing the border (with its obstacles) at a height of 30 m. Its stopping point is at a distance D from the obstacle, comprising: a distance D(sub 1) in regular gliding flight; a distance D(sub 2) in levelling off; a distance D(sub 3) in taxying on the ground. The calculations enable us to make out the following table, which gives an idea of the improvements to be expected in the use of various possible methods of braking in the air and on the ground. digital.library.unt.edu/ark:/67531/metadc65358/
- 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. digital.library.unt.edu/ark:/67531/metadc65098/