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  Partner: UNT Libraries Government Documents Department
 Decade: 1920-1929
 Year: 1925
 Collection: National Advisory Committee for Aeronautics Collection
Pressure distribution over the wings of an MB-3 airplane in flight

Pressure distribution over the wings of an MB-3 airplane in flight

Date: January 1, 1925
Creator: Norton, F H
Description: This investigation was carried out to determine the distribution of load over the wings of a high speed airplane under all conditions of flight. In particular it was desired to find the pressure distribution during level flight, over the portions of the wings in the slipstream and, during violent maneuvers, over the entire wing surface. The method used consisted in connecting a number of holes in the surface of the wings to recording multiple manometers mounted in the fuselage of the airplane. In this way simultaneous records could be taken on all of the holes for any desired length of time. (author).
Contributing Partner: UNT Libraries Government Documents Department
Some problems on the lift and rolling moment of airplane wings

Some problems on the lift and rolling moment of airplane wings

Date: January 1, 1925
Creator: Scarborough, James B
Description: This report deals with the application of the airfoil and twisted wing theory to the calculation of the lift and rolling moment of airplane wings. Most of the results arrived at are strictly true only for wings of elliptic plan form. The investigation aims to give some indications of the accuracy with which the results can be applied to the wing forms in actual use.
Contributing Partner: UNT Libraries Government Documents Department
The influence of the form of a wooden beam on its stiffness and strength III : stresses in wood members subjected to combined column and beam action

The influence of the form of a wooden beam on its stiffness and strength III : stresses in wood members subjected to combined column and beam action

Date: January 1, 1925
Creator: Newlin, J A & Trayer, G W
Description: The general purpose in this study was to determine the stresses in a wooden member subjected to combined beam and column action. What may be considered the specific purpose, as it relates more directly to the problem of design, was to determine the particular stress that obtains at maximum load which, for combined loading, does not occur simultaneously with maximum stress.
Contributing Partner: UNT Libraries Government Documents Department
Determination of turning characteristics of an airship by means of a camera obscura

Determination of turning characteristics of an airship by means of a camera obscura

Date: January 1, 1925
Creator: Crowley, J W , Jr & Freeman, R G
Description: This investigation was carried out by the National Advisory Committee at Langley Field for the purpose of determining the adaptability of the camera obscura to the securing of turning characteristics of airships, and also of obtaining some of those characteristics of the C-7 airship. The method consisted in flying the airship in circling flight over a camera obscura and photographing it at known time intervals. The results show that the method used is highly satisfactory and that for the particular maneuver employed the turning diameter is 1,240 feet, corresponding to a turning coefficient of 6.4, and that the position of zero angle of yaw is at the nose of the airship.
Contributing Partner: UNT Libraries Government Documents Department
The comparison of well-known and new wing sections tested in the variable density wind tunnel

The comparison of well-known and new wing sections tested in the variable density wind tunnel

Date: May 1, 1925
Creator: Higgins, George J
Description: Three groups of airfoils have been tested in the variable density wind tunnel. The first group contains three airfoils. The second group is a systematic series of twenty-seven airfoils. The third group consists of several frequently used wing sections.
Contributing Partner: UNT Libraries Government Documents Department
Discharge characteristics of a high speed fuel injection system

Discharge characteristics of a high speed fuel injection system

Date: February 1, 1925
Creator: Matthews, Robertson
Description: Discussed here are some discharge characteristics of a fuel injection system intended primarily for high speed service. The system consisted of a cam actuated fuel pump, a spring loaded automatic injection valve, and a connecting tube.
Contributing Partner: UNT Libraries Government Documents Department
Pressure distribution on the nose of an airship in circling flight

Pressure distribution on the nose of an airship in circling flight

Date: August 1, 1925
Creator: Fairbanks, Karl J
Description: In recent tests on the pressures occurring on the envelope and control surfaces of the naval airship C-7, it was noted that the pressures on the nose of the airship, while flying in level circling flight, were symmetrically distributed. Such a condition can only occur when the nose of the airship is pointed directly into the wind, and to accomplish this in circling flight, the axis of the airship must then be parallel to the direction of the motion of the nose. The question was raised as to whether the same conditions occur generally on all airships in circling flight. It appears that airships flying in a constant, level, circling flight path will generally head very closely into the wind, and any deviation will be so slight that the distribution of pressure over the nose will be but slightly, if at all, changed from a symmetrical distribution.
Contributing Partner: UNT Libraries Government Documents Department
The effects of shielding the tips of airfoils

The effects of shielding the tips of airfoils

Date: January 1, 1925
Creator: Reid, Elliott G
Description: Tests have recently been made at Langley Memorial Aeronautical Laboratory to ascertain whether the aerodynamic characteristics of an airfoil might be substantially improved by imposing certain limitations upon the air flow about its tips. All of the modified forms were slightly inferior to the plain airfoil at small lift coefficients: however, by mounting thin plates, in planes perpendicular to the span, at the wing tips, the characteristics were improved throughout the range above three-tenths of the maximum lift coefficient. With this form of limitation the detrimental effect was slight; at the higher lift coefficients there resulted a considerable reduction of induced drag and consequently, of power required for sustentation. The slope of the curve of lift versus angle of attack was increased.
Contributing Partner: UNT Libraries Government Documents Department
Standardization tests of NACA no. 1 wind tunnel

Standardization tests of NACA no. 1 wind tunnel

Date: January 1, 1925
Creator: Reid, Elliott G
Description: The tests described in this report were made in the 5-foot atmospheric wind tunnel of the National Advisory Committee for Aeronautics, at Langley Field. The primary objective of collecting data on the characteristics of this tunnel for comparison with those of others throughout the world, in order that, in the future, the results of tests made in all the principle laboratories may be interpreted, compared, and coordinated on a basis of scientifically established relationships, a process hitherto impossible due to the lack of comparable data. The work includes tests of a disk, spheres, cylinders, and airfoils, explorations of the test section for static pressure and velocity distribution, and determination of the variations of air flow direction throughout the operating range of the tunnel. (author).
Contributing Partner: UNT Libraries Government Documents Department
The Flettner rotor ship in the light of the Kutta-Joukowski theory and of experimental results

The Flettner rotor ship in the light of the Kutta-Joukowski theory and of experimental results

Date: October 1, 1925
Creator: Rizzo, Frank
Description: In this paper the fundamental principles of the Flettner rotor ship (Reference I) are discussed in the light of the Kutta-Joukowski theory and available experimental information on the subject. A brief exposition of the Kutta-Joukowski theory is given and the speed of the rotor ship Buckau computed, first by using effective propulsive force obtained by the above theory, and then by direct application of wind tunnel data.
Contributing Partner: UNT Libraries Government Documents Department
Determination of the lift and drag characteristics of an airplane in flight

Determination of the lift and drag characteristics of an airplane in flight

Date: August 1, 1925
Creator: Green, Maurice W
Description: Flight tests to determine lift and drag characteristics are discussed. A review is given of the fundamental principles on which the tests are based and on the forces acting on an airplane in the various conditions of steady flight. Glide with and without propeller thrust and the relation between angle of attack and the indicated airspeed for different conditions of steady flight are discussed. The glide test procedure and the problem of the propeller are discussed.
Contributing Partner: UNT Libraries Government Documents Department
Wire suspensions in wind tunnel experiments

Wire suspensions in wind tunnel experiments

Date: December 1, 1925
Creator: Kerneis, Jean
Description: The elimination of the rigid supports for models and their replacement by wires constitute a great improvement by rendering negligible the interactions of support. There are disadvantages to wire, namely, the aerodynamic resistance is very large and their use is rather difficult because the whole suspension lacks rigidity and easily becomes distorted. We will here investigate the nature of these distortions, evaluate the errors they entail and describe the methods for taking account of or avoiding them.
Contributing Partner: UNT Libraries Government Documents Department
A method for the direct determination of wing-section drag

A method for the direct determination of wing-section drag

Date: November 1, 1925
Creator: Betz, A
Description: In order that the method may be more easily understood, we will first consider the simpler case when there is no lift, but only drag, and when the streamlines at the measuring point behind the obstacle are nearly parallel. Moreover, the flow is assumed not to deviate much from the two-dimensional flow.
Contributing Partner: UNT Libraries Government Documents Department
Theory of flapping flight

Theory of flapping flight

Date: October 1, 1925
Creator: Lippisch, Alexander
Description: Before attempting to construct a human-powered aircraft, the aviator will first try to post himself theoretically on the possible method of operating the flapping wings. This report will present a graphic and mathematical method, which renders it possible to determine the power required, so far as it can be done on the basis of the wing dimensions. We will first consider the form of the flight path through the air. The simplest form is probably the curve of ordinary wave motion. After finding the flight curve, we must next determine the change in the angle of attack while passing through the different phases of the wave.
Contributing Partner: UNT Libraries Government Documents Department
Accelerations in flight

Accelerations in flight

Date: 1925
Creator: Doolittle, J H
Description: This work on accelerometry was done at McCook Field for the purpose of continuing the work done by other investigators and obtaining the accelerations which occur when a high-speed pursuit airplane is subjected to the more common maneuvers. The accelerations obtained in suddenly pulling out of a dive with well-balanced elevators are shown to be within 3 or 4 per cent of the theoretically possible accelerations. The maximum acceleration which a pilot can withstand depends upon the length of time the acceleration is continued. It is shown that he experiences no difficulty under the instantaneous accelerations as high as 7.8 G., but when under accelerations in excess of 4.5 G., continued for several seconds, he quickly loses his faculties.
Contributing Partner: UNT Libraries Government Documents Department
Pitot-static tubes for determining the velocity of air

Pitot-static tubes for determining the velocity of air

Date: February 1, 1925
Creator: Kumbruch, H
Description: On the occasion of the formulation of the rules for testing the efficiency of ventilators and compressors, experiments were instituted by the subcommittee on ventilators for the production of suitable tubes for velocity and pressure measurements.
Contributing Partner: UNT Libraries Government Documents Department
The problem of fuel measurement : the Schiske "Konsummeter"

The problem of fuel measurement : the Schiske "Konsummeter"

Date: May 1, 1925
Creator: Praetorius, K R H
Description: Any measuring device, which immediately indicates the rate of fuel consumption in the desired units, has the advantage of saving considerable time and fuel, besides facilitating the adjustment of the carburetor. The Schiske "Konsummeter" (made by the "PS-Vergaser and Apparatebau A. G.") was designed from the above viewpoint.
Contributing Partner: UNT Libraries Government Documents Department
Strength calculations on airplanes

Strength calculations on airplanes

Date: December 1, 1925
Creator: Baumann, A
Description: Every strength calculation, including those on airplanes, must be preceded by a determination of the forces to be taken into account. In the following discussion, it will be assumed that the magnitudes of these forces are known and that it is only a question of how, on the basis of these known forces, to meet the prescribed conditions on the one hand and the practical requirements on the other.
Contributing Partner: UNT Libraries Government Documents Department
Potential flow in engine valves

Potential flow in engine valves

Date: December 1, 1925
Creator: Eck, Bruno
Description: The extensive applicability of the hydrodynamic theory to the problems of engine construction is clearly shown in the following attempt to determine by exact methods the nature of the flow in valves under variously restricted conditions. Observation shows that two principal kinds of flow occur in simple flat-seated valves. For small valve lifts, the flow is along the horizontal wall and is therefore deflected 90 degrees, but for greater valve lifts the flow separates and forms a free stream, whose angle of deflection naturally increases with increasing lift. Both these kinds of flow can, in fact, be theoretically explained.
Contributing Partner: UNT Libraries Government Documents Department
The light airplane : modern theoretical aerodynamics as applied to light airplane design with a series of charts

The light airplane : modern theoretical aerodynamics as applied to light airplane design with a series of charts

Date: August 1, 1925
Creator: Driggs, Ivan H
Description: T.M. 311 gave a short outline of modern theoretical aerodynamics as applied to light airplane design. This discussion may have been somewhat obscure to the nontechnical reader. A series of charts or curves should serve to clear up such obscurity as well as to more definitely emphasize those quantities most important for each flight characteristic.
Contributing Partner: UNT Libraries Government Documents Department
Pressure Distribution on Joukowski Wings and Graphic Construction of Joukowski Wings

Pressure Distribution on Joukowski Wings and Graphic Construction of Joukowski Wings

Date: October 1, 1925
Creator: Blumenthal, Otto & Trefftz, E.
Description: In the first article, in connection with a lecture on the hydrodynamic basis of flight and the potential flow about a Joukowski wing, the pressure distribution on several wings is computed and plotted. The diagrams of the pressure distributions are presented accompanied with a qualitative discussion of the pressure distribution. In the second article, the the cross-sectional outline (or profile) a Joukowski wing are plotted.
Contributing Partner: UNT Libraries Government Documents Department
Latecoere Air Lines

Latecoere Air Lines

Date: August 1, 1925
Creator: Van Zandt, J Parker
Description: This article presents the observations of the authors on an inspection trip of the Latecoere Air Lines routes from Southern France into North Africa.
Contributing Partner: UNT Libraries Government Documents Department
Preliminary report on British commercial aeronautics

Preliminary report on British commercial aeronautics

Date: July 1, 1925
Creator: Van Zandt, J Parker
Description: This report briefly recounts the history of British commercial aviation and then goes on to look at the equipment, governmental relations, operations, and air traffic.
Contributing Partner: UNT Libraries Government Documents Department
Pressure distribution on fuselage of airplane model

Pressure distribution on fuselage of airplane model

Date: February 1, 1925
Creator: unknown
Description: The method of determining the pressure distribution on the fuselage is described, with special attention to how it is affected by the presence of the wings.
Contributing Partner: UNT Libraries Government Documents Department
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