You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Technical Memorandums
 Collection: National Advisory Committee for Aeronautics Collection
Aerodynamic principles of the direct lifting propeller

Aerodynamic principles of the direct lifting propeller

Date: January 1, 1934
Creator: Schrenk, Martin
Description: The purpose of this report is to make the complicated processes on the direct-lift propeller amenable to analysis and observation. This is accomplished by placing the physical phenomena, starting with the most elementary process, in the foreground, while limiting the mathematical treatment to the most essential in view of the fundamental defects of the theorems. Comparison with model experiments supplements and corroborates the theoretical results.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Research on Fuselages with Rectangular Cross Section

Aerodynamic Research on Fuselages with Rectangular Cross Section

Date: July 1, 1958
Creator: Maruhn, K.
Description: The influence of the deflected flow caused by the fuselage (especially by unsymmetrical attitudes) on the lift and the rolling moment due to sideslip has been discussed for infinitely long fuselages with circular and elliptical cross section. The aim of this work is to add rectangular cross sections and, primarily, to give a principle by which one can get practically usable contours through simple conformal mapping. In a few examples, the velocity field in the wing region and the induced flow produced are calculated and are compared with corresponding results from elliptical and strictly rectangular cross sections.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic safety of airplanes

The aerodynamic safety of airplanes

Date: September 1, 1932
Creator: Kahn, Louis
Description: This report presents several hypotheses regarding airplane safety, mainly concerning the nondimensional coefficient of air, speed, acceleration, and wing area on aerodynamic considerations of safety.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamic wind vane and the inherent stability of airplanes

The aerodynamic wind vane and the inherent stability of airplanes

Date: February 1, 1931
Creator: Lapresle, A
Description: The design of the wind vane described rests on the following line of reasoning: An airplane, originally in equilibrium about its C.G. is assumed to be deflected from this position through an angle (delta)i, the variation (delta)i being so sudden that the path of the C.G. and the airplane speed do not change while it is taking place. The aerodynamic forces acting on the wings, tail surfaces, fuselage, etc., which, as a whole, exerted a zero moment (M(sub G) = 0) about the center of gravity at the instant of equilibrium, now exert a moment M(sub G) not equal to 0.
Contributing Partner: UNT Libraries Government Documents Department
The aerodynamical laboratory of the Vienna Technical High School

The aerodynamical laboratory of the Vienna Technical High School

Date: February 1, 1922
Creator: Katzmayr, R & Kirste, L
Description: We will give here only a short explanation of the operation of the plant and deal principally with the question of what it has accomplished.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics and ballistics

Aerodynamics and ballistics

Date: July 1, 1922
Creator: Burzio, Filippo
Description: Ballistics is a science hundreds of years old and this report is an attempt to show how these older principles can be used in the newer science of aerodynamics.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics of rotating-wing aircraft with blade-pitch control

Aerodynamics of rotating-wing aircraft with blade-pitch control

Date: February 1, 1940
Creator: Pfluger, A
Description: In the present report, with the aid of the usual computation methods, a rotor is investigated the pitch of whose blades is capable of being controlled in such a manner that it varies linearly with the flapping angle. To test the effect of this linkage on the aircraft performance, the theory is applied to an illustrative example.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamics of the Fuselage

Aerodynamics of the Fuselage

Date: December 1, 1942
Creator: Multhopp, H.
Description: The present report deals with a number of problems, particularly with the interaction of the fuselage with the wing and tail, on the basis of simple calculating method's derived from greatly idealized concepts. For the fuselage alone it affords, in variance with potential theory, a certain frictional lift in yawed flow, which, similar to the lift of a wing of small aspect ratio, is no longer linearly related to the angle of attack. Nevertheless there exists for this frictional lift something like a neutral stability point the position of which on oblong fuselages appears to be associated with the lift increase of the fuselage in proximity to the zero lift, according to the present experiments. The Pitching moments of the fuselage can be determined with comparatively great reliability so far as the flow conditions in the neighborhood of the axis of the fuselage can be approximated if the fuselage were absent, which, in general, is not very difficult. For the unstable contribution of the fuselage to the static longitudinal stability of the airplane it affords comparatively simple formulas, the evaluation of which offers little difficulty. On the engine nacelles there is, in addition a very substantial wing moment contribution induced ...
Contributing Partner: UNT Libraries Government Documents Department
Aeroelastic Problems of Airplane Design

Aeroelastic Problems of Airplane Design

Date: November 1, 1956
Creator: Kuessner, H. G.
Description: The technical memorandum briefly summarizes the growth of interest in aeroelastic phenomena as aircraft speed increased and wing designs changed for faster aircraft. Different types of aircraft vibrations are then introduced, and the mathematical basis for the theory behind them is described. Special attention is given to static oscillations, wing flutter, and the flutter of skin panels. The last section of the memorandum deals with the prevention of flutter by design specifications.
Contributing Partner: UNT Libraries Government Documents Department
Aeromechanical experimentation (wind tunnel tests)

Aeromechanical experimentation (wind tunnel tests)

Date: April 1, 1929
Creator: Katzmayr, R
Description: The following report endeavors to show that aeromechanical experimentation has become an important aid to theory.
Contributing Partner: UNT Libraries Government Documents Department
Aeronautic instruction in Germany

Aeronautic instruction in Germany

Date: November 1, 1921
Creator: Bouche, Henri
Description: This report contains a list of the courses relating to aeronautics announced in Germany, both in the technical high schools and in the universities.
Contributing Partner: UNT Libraries Government Documents Department
Aeronautic instruments

Aeronautic instruments

Date: February 1, 1924
Creator: Koppe, H & Everling, E
Description: The development of aeronautic instruments. Vibrations, rapid changes of the conditions of flight and of atmospheric conditions, influence of the air stream all call for particular design and construction of the individual instruments. This is shown by certain examples of individual instruments and of various classes of instruments for measuring pressure, change of altitude, temperature, velocity, inclination and turning or combinations of these.
Contributing Partner: UNT Libraries Government Documents Department
Aeronautic insurance

Aeronautic insurance

Date: March 1, 1922
Creator: Neal, Erik
Description: The problem of insuring the emerging commercial aeronautic industry is detailed. The author also motes that a complete solution cannot be obtained until the necessary statistics are compiled.
Contributing Partner: UNT Libraries Government Documents Department
Aeronautical education and research at the Swiss Institute of Technology in Zurich

Aeronautical education and research at the Swiss Institute of Technology in Zurich

Date: April 1, 1931
Creator: Karner, L & Ackeret, J
Description: Progress in the scientific and practical fields of aviation has caused the Swiss Institute of Technology to organize lectures and practical training courses in all three branches of aeronautics and to found centers of scientific research, laboratories, etc., in order to supply the government and industries with scientifically and technically trained engineers.
Contributing Partner: UNT Libraries Government Documents Department
The aeronautical laboratory of the Stockholm Technical Institute

The aeronautical laboratory of the Stockholm Technical Institute

Date: March 1, 1935
Creator: Malmer, Ivar
Description: This report presents a detailed analysis and history of the construction and operation of the aeronautical laboratory of the Stockholm Technical Institute. Engines and balances are discussed and experimental results are also given.
Contributing Partner: UNT Libraries Government Documents Department
Aeronautical museums

Aeronautical museums

Date: November 1, 1922
Creator: Warner, Edward P
Description: Different methods of presenting aeronautical artifacts are examined.
Contributing Partner: UNT Libraries Government Documents Department
Aeronautical record : no. 1 (to June, 1923)

Aeronautical record : no. 1 (to June, 1923)

Date: December 1, 1923
Creator: unknown
Description: "...considerations have prompted us to pay special attention to the development of aeronautical industries and aerial navigation as a commercial enterprise and to publish an analytical review of events in the aeronautical world and of the attendant problems.".
Contributing Partner: UNT Libraries Government Documents Department
Air admixture to exhaust jets

Air admixture to exhaust jets

Date: July 1, 1953
Creator: Sanger, Eugen
Description: The problem of thrust increase by air admixture to exhaust jets of rockets, turbojet, ram- and pulse-jet engines is investigated theoretically. The optimum ratio of mixing chamber pressure to ambient pressure and speed range for thrust increase due to air admixture is determined for each type of jet engine.
Contributing Partner: UNT Libraries Government Documents Department
Air cooling : an experimental method of evaluating the cooling effect of air streams on air-cooled cylinders

Air cooling : an experimental method of evaluating the cooling effect of air streams on air-cooled cylinders

Date: May 1, 1927
Creator: Alcock, J F
Description: In this report is described an experimental method which the writer has evolved for dealing with air-cooled engines, and some of the data obtained by its means. Methods of temperature measurement and cooling are provided.
Contributing Partner: UNT Libraries Government Documents Department
Air-flow experiments

Air-flow experiments

Date: May 1, 1924
Creator: Wieselsberger, C
Description: This report describes the apparatus used to take air-flow photographs. The photographs show chiefly the spiral course of the lines of flow near the tip of the wing. They constitute therefore a visual presentation of the phenomena covered by airfoil theory.
Contributing Partner: UNT Libraries Government Documents Department
Air forces and air-force moments at large angles of attack and how they are affected by the shape of the wing

Air forces and air-force moments at large angles of attack and how they are affected by the shape of the wing

Date: July 1, 1930
Creator: Fuchs, Richard & Schmidt, Wilhelm
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Air Forces Exerted on Streamlined Bodies with Round or Square Cross- Sections, When Placed Obliquely to the Airstream

Air Forces Exerted on Streamlined Bodies with Round or Square Cross- Sections, When Placed Obliquely to the Airstream

Date: June 1, 1924
Creator: Wieselsberger, C
Description: The question of behavior of a streamlined body with round or square cross-sections is of importance in determining the shape to give an airplane fuselage. It is our task here to show how the lift and drag are affected, with the object placed obliquely to the air stream.
Contributing Partner: UNT Libraries Government Documents Department
Air forces on airfoils moving faster than sound

Air forces on airfoils moving faster than sound

Date: June 1, 1925
Creator: Ackeret, J
Description: We are undertaking the task of computing the air forces on a slightly cambered airfoil in the absence of friction and with an infinite aspect ratio. We also assume in advance that the leading edge is very sharp and that its tangent lies in the direction of motion.
Contributing Partner: UNT Libraries Government Documents Department
Air reactions to objects moving at rates above the velocity of sound with application to the air propeller

Air reactions to objects moving at rates above the velocity of sound with application to the air propeller

Date: November 1, 1922
Creator: Reed, S Albert
Description: There has been a tradition general among aeronautical engineers that a critical point exists for tip speeds at or near the velocity of sound, indicating a physical limit in the use of propellers at higher tip speeds; the idea being that something would occur analogous to what is known in marine propellers as cavitation. In the examination of the physics pertaining to both propellers and projectiles moving at or above 1100 feet per second, the conclusion was reached by the author that there is no reason for the existence of such a critical point and that, if it had been noted by observers it was not inherent in the phenomena revealed, but rather due to a particular shape or proportion of the projectile and that, with properly proportioned sections, it would not exist.
Contributing Partner: UNT Libraries Government Documents Department