National Advisory Committee for Aeronautics (NACA) - 124 Matching Results

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An investigation of the characteristics of steel diaphragms for automatic fuel-injection valves
"This research on steel diaphragms was undertaken at the Langley Memorial Aeronautical Laboratory, as a part of a general investigation on fuel injection engines for aircraft. The work determined the load-deflection, load- deformation and hysteresis characteristics for single diaphragms having thicknesses from 0.00s inch to 0.012 inch, and for similar diaphragms tested in multiple having total thicknesses from 0.012 inch to 0.180 inch. The elastic limit loads and deflections, and rupture points of single diaphragms were also determined. Some work was done on diaphragms having central orifices in order to determine the effect of orifice diameter upon the load deflection characteristics" (p. 1).
Propeller Design: Practical Application of the Blade Element Theory 1
"This report is the first of a series of four on propeller design and contains a description of the blade elements or modified Drzewiecke theory as used in the Bureau of Aeronautics, U.S. Navy Department. Blade interference corrections are used which were taken from R.& M. NO. 639 of the British Advisory Committee for Aeronautics. The airfoil characteristics used were obtained from tests of model propellers, not from tests of model wings" (p. 1).
Propeller Design: Extension of Test Data on a Family of Model Propellers by Means of the Modified Blade Element Theory 2
This report is the second of a series of four on propeller design, and describes the method used to extend the data obtained from tests on a family of thirteen model propellers to include all propellers of the same form likely to be met in practice. This necessitates the development of a method of propeller analysis which when used to calculate the powers and efficiencies gives results which check the tests throughout their range.
Propeller Design - A Simple System Based on Model Propeller Test Data -III
"This report, the third of a series of four, describes a simple system for designing propellers of a standard form. In this report, the system is based on tests of a family of model propellers of standard Navy form, the data from which have been extended by means of calculations to cover the complete range likely to be found in practice. However, it can be worked out for any family having propellers of one general form" (p. 1).
Propeller Design - A Simple Method for Determining the Strength of Propellers - IV
"The object of this report, the last of a series of four on propeller design, is to describe a simple method for determining whether the strength of a propeller of a standard form is sufficient for safe operation. An approximate method of stress analysis is also given" (p. 1).
Steam Power Plants in Aircraft
"The employment of steam power plants in aircraft has been frequently proposed. Arguments pro and con have appeared in many journals. It is the purpose of this paper to make a brief analysis of the proposal from the broad general viewpoint of aircraft power plants. Any such analysis may be general or detailed" (p. 1).
The N.A.C.A. CYH airfoil section
The NACA CYH airfoil section is described and its aerodynamic characteristics are given as tested in the NACA variable density wind tunnel at twenty atmosphere pressure. This section has a low drag, a high maximum lift, and a small travel of center of pressure.
The Spacing of Orifices for the Measure of Pressure Distributions
"The following report has been prepared for publication by the NACA. Suitable locations of orifices for the measurement of pressure distributions have been discussed. Tables are given for quickly laying out these locations and for quickly and easily computing the resultant air forces from the result of the measurements" (p. 1).
The Resistance to the Steady Motion of Small Spheres in Fluids
"There seems to be little reliable information conveniently available as to the resistance encountered by small spheres moving steadily at moderate speeds in fluids. The present paper, while presenting nothing new in the way of either theory or data, has three objects: first to show that published data are sufficient to furnish approximate information; second to present this information in form convenient for computation; and, third to indicate where further research is needed" (p. 1).
The Lateral Failure of Spars
It was concluded that after the critical span or depth-breadth ratio has been reached, the modulus of rupture varies approximately inversely as the first power of the span and of the depth-breadth ratio. The direction of the lateral deflection is alternate between successive supports. For this reason, we believe that rib spacing along the spar is more important in reducing lateral deflection than the distance between supports at the strut points.
N.A.C.A. Flight-Path Angle and Air-Speed Recorder
"A new trailing bomb-type instrument for photographically recording the flight-path angle and air speed of aircraft in unaccelerated flight is described. The instrument consists essentially of an inclinometer, air-speed meter and a film-drum case. The inclinometer carries an oil-damped pendulum which records optically the flight-path angle upon a rotating motor-driven film drum. The air-speed meter consists of a taut metal diaphragm of high natural frequency which is acted upon by the pressure difference of a Prandtl type Pitot-static tube" (p. 1).
Tests of Several Bearing Materials Lubricated by Gasoline
"This investigation on the relative wear of several bearing materials lubricated by gasoline was conducted at the Langley Memorial Aeronautical Laboratory, as part of a general research on fuel injection engines for aircraft. The specific purpose of the work was to find a durable bearing material for gear pumps to be used for the delivery of gasoline and diesel engine fuel oil at moderate pressures to the high pressure pumps of fuel injection engines" (p. 1).
The characteristics of the N.A.C.A. M-12 airfoil section
The data obtained on the NACA M-12 airfoil, tested at twenty atmosphere density in the NACA variable density wind tunnel, have been extended by additional tests at one and at twenty atmospheres under improved conditions. The results of these tests are given. Considerable scale effect was found.
Navy Propeller Section Characteristics as Used in Propeller Design
"This report contains artificial aerodynamic characteristics of a set of propeller sections to be used in designing propellers by means of the blade element theory. Characteristics computed from model propeller tests for a single section are extended to cover sections of Navy propeller sections at high Reynolds Number in the variable density tunnel of the NACA" (p. 1).
Report on Tests of Metal Model Propellers in Combination With a Model VE-7 Airplane
This report, prepared at the request of the NACA, describes tests of three metal model propellers, in a free air stream and in front of a model of a VE-7 airplane. The effect of introducing the model airplane is shown to be an increase in thrust and power coefficients and efficiency at small slip, and a decrease in the same at large slip.
Test of a Model Propeller With Symmetrical Blade Sections
"This report, prepared at the request of NACA, gives the results of tests on a model propeller having blade sections with form of Gottingen airfoil no. 409. The model is shown to have a dynamic pitch practically equal to the nominal or geometrical pitch, and a somewhat higher efficiency but lower coefficient than would be expected of a propeller of more conventional sections" (p. 1).
The Drag of Airships : II - Drag of Bare Hulls
"The extension of wind tunnel tests of models of airship hulls to full scale requires an extension from a VL of the order of less than 500 sq.ft./sec., to that of 80000 sq.ft./sec., where V = air speed, feet per second, L = length in feel of the particular form of hull. The reason for this research was to furnish the airship designer with a method for finding the VL curve of any conventional type of hull, using data obtained from actual performance of airships flown prior to 1926" (p. 1).
Influence of the Orifice on Measured Pressures
"The influence of different orifices on the result of measuring the same pressure distributions is the subject of this note. A circular cylinder is exposed to an air stream perpendicular to its axis and its pressure distribution is repeatedly determined. The pressures measured on the downstream half of the cylinder do not change for the orifice sizes used in the tests" (p. 1).
Suggestions for Popularizing Civil Aviation
The public generally is taking very little interest in the progress of Civil Aviation, and the time has come to educate the public in aeronautics and to make them realize the far-reaching importance of air transport. Briefly, the whole problem resolves itself into discovering and applying means for bringing some of the many aspects and effects of civil aviation into the everyday lives of the public. The report suggests three principal groups of methods: (1) Bring aviation into daily contact with the public. (2) Bring the public into daily contact with aviation. (3) General publicity.
The New De Havilland Commercial Airplane: The D.H. 66 With Three Bristol "Jupiter" Engines
The D.H. 66, constructed at Stag Lane Works of the De Haviland Aircraft Company built for Imperial Airways, Ltd. The fuselage has an all steel construction while the wings are made with box spars of wood and spruce ribs. It has a biplane tail and encloses the stabilizer trimming gear in a casing which serves to streamline the rear portion of the fuselage, but which is not part of the main structure. It weighs 9060 lbs. empty and 2500 lbs. after fueling with a total loaded weight of 14,700 lbs.
The Avro "Avian" Airplane: 65 HP. Armstrong-Siddeley "Genet" Engine
The Avro Avian, designed by Mr. Chadwick of A.V. Roe & Co., Ltd. has a very low structural weight (estimated at 750 lbs. empty) but with sufficient structural integrity to be eligible of an "Aerobatics" certificate from the British Air Ministry. It can be configured as a monoplane, or a biplane with seaplane floats. It is designed for economical production.
The Farman Commercial Airplane "Jabiru"
Circular presenting a description of the Farman Jabiru F 3X, which was designed to satisfy the requirements of the aerial-navigation companies. Details regarding the power, wing, fuselage, landing gear, construction, engines, fuel tanks, characteristics, performance, drawings, and photographs are provided.
Albatros Commercial Airplane L 73
The Albatros was a two engine commercial biplane carrying 2 pilots, eight passengers, and 160 KG of baggage. The framework is metal, the wings having plywood and fabric over the steel tubing. The L 73 was the first 2 engine biplane to be made in Germany.
German Training Airplane, Arado "Ar. S.I."
Circular presenting a description of the Arado Ar. S.I., which is a wireless biplane that is both physically attractive and highly performing. A description of the components, controls, construction, characteristics, flying qualities, drawings, and photographs are provided.
All-Metal Junkers Airplane, Type F 13
Circular describing the all-metal Junkers airplane, specifically the F 13 type. The primary characteristics of the airplanes are the thick cantilever Junkers wing without stay-wires and the all-metal construction. A description of the design, flight characteristics, and some photographs are provided.
Two 'Gloster' Airplanes: The 'Grouse II,' - Two-Seat Training Airplane, The 'Grebe II,' Single-Seat Fighter
Circular presenting a description of two airplanes created by the Gloucestershire Aircraft Company, the "Grouse II" and the "Grebe II". A description of the design and flight characteristics as well as the blueprints and photographs of the aircraft are provided.
The Drag of Airships I
Report presenting an examination of the drag of airships in order to design more functional aircraft and to obtain information for future research.
Wind Tunnel Standardization Disk Drag
Note presenting the resistances of a series of three similar disks placed normal to the wind as determined in the atmospheric wind tunnel. The curves of drag coefficient plotted against Reynolds number for this tunnel show discrepancies between overlapping values which are to be attributed to the presence of the tunnel walls.
Effect of Protruding Gasoline Tanks Upon the Characteristics of an Airfoil
Note presenting an investigation to determine the effect of a gasoline tank protruding from the center section of a wing on the aerodynamic characteristics of the wing. The results are presented in the form of polar curves, curves of D/L against lift coefficient, and the curves of lift and drag coefficient against the angle of attack.
Resistance of a fifteen-centimeter disk
"The results of this test show that the dynamic scale has very little effect on the drag coefficient of a disk over a wide range of Reynolds Number. A comparison of these results with those of tests made on a series of disks at Göttingen University furnishes a good check on the method of testing in this tunnel" (p. 1).
The effect of tube length upon the recorded pressures from a pair of static orifices in a wing panel
Report presenting an investigation to determine the effect of tubing length on the indicated pressure values as ascertained in the pressure distribution measurements on the PW-9. The purpose was to determine the percentage of error in the pressure readings which might be caused by various lengths of tubing between the pressure orifices and pressure cell at the manometer. The differences in head caused by variations in the length of tubing are small, the lowest recorded being zero, the highest 2.7 percent.
Farman Monoplane F.170: Commercial Airplane with One 500 HP. Farman Engine
The F.170's engine has won world endurance tests in 1924 and in 1925. It has a semi-thick wing, rigidly braced by oblique struts. This wing is embedded in the top of the fuselage and measures 16.1 by 3.6 meters. The F.170 has a passenger compartment seating eight.
Heinkel Airplane H.D. 39 for Carrying Newspapers
Circular presenting a description of the Heinkel Airplane H.D. 39, which is a postal airplane that can be used to carry newspapers. Details regarding the design, controls, equipment arrangement, fuel, and flying characteristics are provided.
The Blackburn "Sprat": A Training Airplane Convertible Into Landplane or Seaplane
The Sprat is similar the Blackburn Swift and Dart models but is designed as a trainer. It is powered with a smaller 275 HP Rolls-Royce Falcon engine. It is a 2 seat biplane with equal sized upper and lower wings. It can quickly convert from a land to a seaplane.
The Albatros L 72A: A German Newspaper Carrier With Slotted Wings
The Albatros 72A is a normal tractor biplane specifically designed to deliver newspapers by dropping them overboard in bundles for ground transport to pick up. It has a 42 ft. wingspan, and a 220 HP B.M.W. engine.
Rohrbach All Metal Commercial Airplane Ro VIII "Roland"
With three 230 HP. engines and all metal construction, the Roland, Rohrbach VIII is a passenger aircraft with seating for two pilots and 10 passengers. Details of the components, characteristics, performance data, drawings, and photographs are provided.
The Bristol "Badminton" Airplane
The Bristol Badminton, Type 99 airplane has a radial aircooled engine (a Bristol Jupiter 9 cylinder 450 HP.) and three fuel tanks. It is a single seat biplane weighing 1,840 lbs. empty and 2,460 lbs. loaded. A description of the design, components, photographs, and drawings are provided.
Experiments With an Airfoil From Which the Boundary Layer Is Removed by Suction
"Our attempts to improve the properties of airfoils by removing the boundary layer by suction, go back to 1922. The object of the suction is chiefly to prevent the detachment of the boundary layer from the surface of the airfoil. At large angles of attack, such detachment prevents the attainment of the great lift promised by the theory, besides greatly increasing the drag, especially of thick airfoils. This report gives results of those experiments" (p. 1).
Tail Planes
This report presents methods by which the cells of large commercial airplanes may be reduced. The tail of large airplanes represent an area where considerable improvement in weight and size reduction can be attained.
Mixing and Ignition in Supercharged Engines
Memorandum presenting two principal methods of mixing for carburetor engines, one using a suction carburetor and the other using a pressure carburetor. An investigation of the spark plugs in the engines and how to design them so they can resist high levels of heat is also provided.
Behm Acoustic Sounder for Aircraft
The Behm acoustic sounder for aircraft enables the barometric determination for the altitude by night or fog and therefore promises to prove of great importance in safeguarding air traffic.
Protection of wooden airplane parts against moisture by means of varnish
The objects of the experiments herein described were to test the protection afforded by Valspar oil varnish against the absorption of moisture by wooden airplane parts and the consequent changes in their elastic properties and to compare some of the best Dutch varnishes with Valspar.
Change of 180 Degrees in the Direction of a Uniform Current of Air
In the construction of aerodynamic tunnels, it is a very important matter to obtain a uniform current of air in the sections where measurements are to be made. The straight type ordinarily used for attaining a uniform current and generally recommended for use, has great defects. If we desire to avoid these defects, it is well to give the canals of the tunnel such a form that the current, after the change of direction of its asymptotes, approximates a uniform and rectilinear movement. But for this, the condition must be met that at no place does the flow exceed the maximum velocity assumed, equal to the velocity in the straight parts of the canal.
Kirsten-Boeing Propeller
The advantages of the Kirsten-Boeing propeller consist essentially in the adjustability of the thrust in any desired direction, in the plane perpendicular to the axis of rotation of the system, and in its high efficiency. The propeller, which greatly resembles the paddle wheels used on river steamers, differs fundamentally from the latter, in that all the blades work simultaneously in the fluid medium (air or water).
Approximate Calculation of the Static Longitudinal Stability of Airplanes
It seems desirable to have some simple method for calculating quickly and with sufficient accuracy: 1) the correct position of the center of gravity; 2) the requisite tail-group dimensions; 3) and the course of the wing and tail-group moments. In out deductions, we will first replace the biplane (disregarding the effect of stagger, decalage and induced drag) by an equivalent monoplane, whose dimensions and position in space can be approximately determined in a simple manner.
Experiments on Autorotation
This article deals principally with Professor Bairstow's experiments on autorotation, in which the wing is free to rotate about an axis in its plane of symmetry, which axis is parallel with the direction of the wind.
The fundamental principles of high-speed semi-diesel engines. Part 2: a discussion of the semi-diesel principle and its application to various types of solid-injection engines
Three high-speed semi-diesel engines are examined through the use of indicator diagrams. Different fuel nozzles and fuels are investigated and conclusions are drawn.
The fundamental principles of high-speed semi-diesel engines. Part 3: a discussion of fuel mixing and ignition, with special reference to engines with precombustion chambers
A continuation of the discussion and overview of the present state of development of high-speed semi-diesel engines.
Flight Tests on Airplanes
This report presents test procedures, methods, and instruments for flight testing of aircraft. Dynamic-pressure gauges are discussed at length.
Experiments With a Sphere From Which the Boundary Layer Is Removed by Suction
The task of removing the boundary layer by suction consists in producing, in place of the ordinary flow with the formation of vortices, another kind of flow in which the vortices are eliminated by drawing small quantities of fluid from certain points on the surface into the interior of the body. The experiments with a sphere, which constitute the subject of this report, were made early in the present year .
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