You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Decade: 1920-1929
 Serial/Series Title: NACA Technical Notes
 Collection: National Advisory Committee for Aeronautics Collection
The 300 H.P. Benz Aircraft Engine

The 300 H.P. Benz Aircraft Engine

Date: January 1921
Creator: Heller, A.
Description: This report provides a description of the Benz 300 H.P. aircraft engine containing 12 cylinders placed at a 60° angle. It includes a detailed description of the development of the constructional points, particularly the cylinders, pistons, and connecting rods, as well as the engine fitting, lubrication, oil pumps, bearings, oil tank, fuel pump, carburetors, and cooling system. There are seven pages of illustrative figures at the end of the report.
Contributing Partner: UNT Libraries Government Documents Department
N.A.C.A. control position recorder

N.A.C.A. control position recorder

Date: May 1922
Creator: Norton, F H
Description: A new instrument is described which is capable of simultaneously recording the position of the three controls of an airplane. The records are taken photographically on a standard N.A.C.A. film drum and the instrument can be quickly installed in any airplane.
Contributing Partner: UNT Libraries Government Documents Department
N.A.C.A. Langley field wind tunnel apparatusthe tilting manometer

N.A.C.A. Langley field wind tunnel apparatusthe tilting manometer

Date: January 1921
Creator: Norton, F H & Bacon, D L
Description: A description is given of a tilting manometer designed to meet the requirements of a manometer for use in the wind tunnel at the Langley Memorial Aeronautical Laboratory. This gauge was designed to meet the requirements of a manometer in use in connection with a static pressure plate to indicate the wind speed in the tunnel. The requirements are noted. The sensitivity of the gauge must be made inversely proportional to the pressure to be measured. The gauge must be accurately and quickly set for any desired pressure. When set at the desired pressure, the extent of variation between the existing and the desired pressures may be readily estimated. In fact, this manometer is quick to adjust, is easy to read, always has the meniscus in the same position, and accurately indicates a large range of air speeds on what is a comparatively compact instrument.
Contributing Partner: UNT Libraries Government Documents Department
N.A.C.A. recording  air speed meter

N.A.C.A. recording air speed meter

Date: October 1921
Creator: Norton, F H
Description: A new type of air speed meter is described which was designed by the technical staff of the National Advisory Committee for Aeronautics. The instrument consists essentially of a tight metal diaphragm of high natural period which is acted upon by the pressure difference of a pitot-static head. The resulting deflection of this diaphragm is recorded optically on a moving film.
Contributing Partner: UNT Libraries Government Documents Department
Absolute coefficients and the graphical representation of airfoil characteristics

Absolute coefficients and the graphical representation of airfoil characteristics

Date: June 1921
Creator: Munk, Max
Description: It is argued that there should be an agreement as to what conventions to use in determining absolute coefficients used in aeronautics and in how to plot those coefficients. Of particular importance are the absolute coefficients of lift and drag. The author argues for the use of the German method over the kind in common use in the United States and England, and for the Continental over the usual American and British method of graphically representing the characteristics of an airfoil. The author notes that, on the whole, it appears that the use of natural absolute coefficients in a polar diagram is the logical method for presentation of airfoil characteristics, and that serious consideration should be given to the advisability of adopting this method in all countries, in order to advance uniformity and accuracy in the science of aeronautics.
Contributing Partner: UNT Libraries Government Documents Department
Absolute dimensions of Karman vortex motion

Absolute dimensions of Karman vortex motion

Date: January 1923
Creator: Heisenberg, Werner
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Adaptation of aeronautical engines to high altitude flying

Adaptation of aeronautical engines to high altitude flying

Date: May 1, 1923
Creator: Kutzbach, K
Description: Issues and techniques relative to the adaptation of aircraft engines to high altitude flight are discussed. Covered here are the limits of engine output, modifications and characteristics of high altitude engines, the influence of air density on the proportions of fuel mixtures, methods of varying the proportions of fuel mixtures, the automatic prevention of fuel waste, and the design and application of air pressure regulators to high altitude flying. Summary: 1. Limits of engine output. 2. High altitude engines. 3. Influence of air density on proportions of mixture. 4. Methods of varying proportions of mixture. 5. Automatic prevention of fuel waste. 6. Design and application of air pressure regulators to high altitude flying.
Contributing Partner: UNT Libraries Government Documents Department
Aeronautical instruments

Aeronautical instruments

Date: June 1, 1923
Creator: Bennewitz, Kurt
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air flow investigation for location of angle of attack head on a JN4h airplane

Air flow investigation for location of angle of attack head on a JN4h airplane

Date: August 1, 1925
Creator: Freeman, R G
Description: The technical staff of the NACA at Langley Field, has made a series of free flight tests with a JN4h airplane in order to find the best place for an instrument for measuring the angle of attack. A "neutral zone" was found where the air remains either at rest relative to the undisturbed air beyond the influence of the airplane, or is set in motion parallel to the motion of the airplane. This zone is about midway between the two wings and slightly in front of, or at the vertical plane through the leading edges of the wings but the exact position as well as the outlines of the zone varies considerably as the conditions of flight change.
Contributing Partner: UNT Libraries Government Documents Department
Air force and three moments for F-5-L Seaplane

Air force and three moments for F-5-L Seaplane

Date: February 1, 1922
Creator: unknown
Description: A model of the F-5-L seaplane was made, verified, and tested at 40 miles an hour in the 8' x 8' tunnel for lift and drag, also for pitching, yawing and rolling moments. Subsequently, the yawing moment test was repeated with a modified fin. The results are reported without VL scale correction.
Contributing Partner: UNT Libraries Government Documents Department
The air propeller, its strength and correct shape

The air propeller, its strength and correct shape

Date: February 1, 1923
Creator: Dietsius, H
Description: It is possible to give a propeller such a shape that, under given conditions, viz., a definite speed of revolution and flying speed, the bending stresses in the blades will assume quite an insignificant magnitude.
Contributing Partner: UNT Libraries Government Documents Department
Air resistance measurements on actual airplane parts

Air resistance measurements on actual airplane parts

Date: November 1, 1923
Creator: Weiselsberger, C
Description: For the calculation of the parasite resistance of an airplane, a knowledge of the resistance of the individual structural and accessory parts is necessary. The most reliable basis for this is given by tests with actual airplane parts at airspeeds which occur in practice. The data given here relate to the landing gear of a Siemanms-Schuckert DI airplane; the landing gear of a 'Luftfahrzeug-Gesellschaft' airplane (type Roland Dlla); landing gear of a 'Flugzeugbau Friedrichshafen' G airplane; a machine gun, and the exhaust manifold of a 269 HP engine.
Contributing Partner: UNT Libraries Government Documents Department
Aircraft engine design

Aircraft engine design

Date: January 1, 1925
Creator: Wilson, E E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Airfoil lift with changing angle of attack

Airfoil lift with changing angle of attack

Date: September 1, 1927
Creator: Reid, Elliott G
Description: Tests have been made in the atmospheric wind tunnel of the National Advisory Committee for Aeronautics to determine the effects of pitching oscillations upon the lift of an airfoil. It has been found that the lift of an airfoil, while pitching, is usually less than that which would exist at the same angle of attack in the stationary condition, although exceptions may occur when the lift is small or if the angle of attack is being rapidly reduced. It is also shown that the behavior of a pitching airfoil may be qualitatively explained on the basis of accepted aerodynamic theory.
Contributing Partner: UNT Libraries Government Documents Department
Airplane balance

Airplane balance

Date: June 1, 1921
Creator: Huguet, L
Description: The authors argue that the center of gravity has a preponderating influence on the longitudinal stability of an airplane in flight, but that manufacturers, although aware of this influence, are still content to apply empirical rules to the balancing of their airplanes instead of conducting wind tunnel tests. The author examines the following points: 1) longitudinal stability, in flight, of a glider with coinciding centers; 2) the influence exercised on the stability of flight by the position of the axis of thrust with respect to the center of gravity and the whole of the glider; 3) the stability on the ground before taking off, and the influence of the position of the landing gear. 4) the influence of the elements of the glider on the balance, the possibility of sometimes correcting defective balance, and the valuable information given on this point by wind tunnel tests; 5) and a brief examination of the equilibrium of power in horizontal flight, where the conditions of stability peculiar to this kind of flight are added to previously existing conditions of the stability of the glider, and interfere in fixing the safety limits of certain evolutions.
Contributing Partner: UNT Libraries Government Documents Department
Airplane crashes: engine troubles : a possible explanation

Airplane crashes: engine troubles : a possible explanation

Date: March 1, 1921
Creator: Sparrow, Stanwood W
Description: The aim was to bring attention to what might be the cause of some aircraft accidents for which there was no satisfactory explanation. The author notes that in testing aircraft accidents at the Bureau of Standards, it happened frequently that the engine performance became erratic when the temperature of the air entering the carburetor was between 0 C and 20 C. Investigation revealed the trouble to have been caused by the formation and collection of snow somewhere between the entrance to the carburetor and the manifold, probably at the throttle. Proof scarcely less convincing was obtained during engine tests. The results of such engine tests are described. Granting that the loss of power and the sudden increases in power were caused by the condensation of moisture from the air and the subsequent formation of snow, two solutions proved effective. The removal of the moisture or an increase in temperature cured the problem.
Contributing Partner: UNT Libraries Government Documents Department
Airplane performance as influenced by the use of a supercharged engine

Airplane performance as influenced by the use of a supercharged engine

Date: May 1, 1920
Creator: De Bothezat, George
Description: The question of the influence of a supercharged engine on airplane performance is treated here in a first approximation, but one that gives an exact idea of the advantage of supercharging. Considered here is an airplane that climbs first with an ordinary engine, not supercharged, and afterwards climbs with a supercharged engine. The aim is to find the difference of the ceilings reached in the two cases. In the case of our figure, the ceiling from 25,000 feet is increased to 37,000 feet, the supercharging maintaining the power only up to 20,000 feet. This makes, in comparison with an engine without supercharging, an increase of about 50 percent.
Contributing Partner: UNT Libraries Government Documents Department
Airplane superchargers

Airplane superchargers

Date: May 1, 1921
Creator: Noack, W G
Description: Discussed here are the principles and operation of aircraft engine superchargers used to maintain and increase engine power as aircraft encounter decreases in the density of air as altitude rises. Details are given on the design and operation of the centrifugal compressors. A method is given for calculating the amount of power needed to drive a compressor. The effects of the use of a compressor on fuel system operation and design are discussed. Several specific superchargers that were in operation are described.
Contributing Partner: UNT Libraries Government Documents Department
Airplanes in horizontal curvilinear flight

Airplanes in horizontal curvilinear flight

Date: January 1, 1924
Creator: Kann, Heinrich
Description: War airplanes require not only high speed and the ability to climb rapidly, but also the ability to transverse sharp curves quickly. Here, an attempt is made to give a simple method of calculating horizontal curvilinear flight. A method for determining the area of the aileron and rubber surfaces are also indicated. The discussion given here applies primarily to single and two-seater airplanes, although it can be extended to larger airplanes.
Contributing Partner: UNT Libraries Government Documents Department
An altitude chamber for the study and calibration of aeronautical instruments

An altitude chamber for the study and calibration of aeronautical instruments

Date: November 1, 1925
Creator: Reid, J E & Kirchner, Otto E
Description: The design and construction of an altitude chamber, in which both pressure and temperature can be varied independently, was carried out by the NACA at the Langley Memorial Aeronautical Laboratory for the purpose of studying the effects of temperature and pressure on aeronautical research instruments. Temperatures from +20c to -50c are obtained by the expansion of CO2from standard containers. The chamber can be used for the calibration of research instruments under altitude conditions simulating those up to 45,000 feet. Results obtained with this chamber have a direct application in the design and calibration of instruments used in free flight research.
Contributing Partner: UNT Libraries Government Documents Department
Analysis of Dr. Schaffran's propeller model tests

Analysis of Dr. Schaffran's propeller model tests

Date: September 1, 1923
Creator: Munk, Max M
Description: This analysis was made in the same way as Dr. Durand's tests. Only the thrust is examined.
Contributing Partner: UNT Libraries Government Documents Department
Aneroid investigations in Germany

Aneroid investigations in Germany

Date: October 1, 1921
Creator: Hersey, M D
Description: None
Contributing Partner: UNT Libraries Government Documents Department
The arithmetic of distribution in multi-cylinder engines

The arithmetic of distribution in multi-cylinder engines

Date: October 1, 1923
Creator: Sparrow, Stanwood S
Description: None
Contributing Partner: UNT Libraries Government Documents Department
An automatic speed control for wind tunnels

An automatic speed control for wind tunnels

Date: February 1, 1928
Creator: Zahm, A F
Description: Described here is an automatic control that has been used in several forms in wind tunnels at the Washington Navy Yard. The form now in use with the 8-foot tunnel at the Navy Yard is considered here. Details of the design and operation of the automatic control system are given. Leads from a Pitot tube are joined to an inverted cup manometer located above a rheostat. When the sliding weight of this instrument is set to a given notch, say for 40 m.p.h, the beam tip vibrates between two electric contacts that feed the little motor. Thus, when the wind is too strong or too weak, the motor automatically throws the rheostat slide forward and backward. If it failed to function well, the operator would notice the effect on his meniscus, and would operate the hand control by merely pressing the switch.
Contributing Partner: UNT Libraries Government Documents Department
FIRST PREV 1 2 3 4 5 NEXT LAST