You limited your search to:

  Partner: UNT Libraries Government Documents Department
 Serial/Series Title: NACA Technical Memorandums
 Collection: National Advisory Committee for Aeronautics Collection
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 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 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 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 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
Air traffic

Air traffic

Date: May 1, 1922
Creator: Sudre, G
Description: This report presents a recounting of the steps taken by France to establish national and international regulation over air traffic.
Contributing Partner: UNT Libraries Government Documents Department
Air transport

Air transport

Date: January 1, 1924
Creator: Page, F Handley
Description: I purpose (sic) in this paper to deal with the development in air transport which has taken place since civil aviation between England and the Continent first started at the end of August 1919. A great deal of attention has been paid in the press to air services of the future, to the detriment of the consideration of results obtained up to the present.
Contributing Partner: UNT Libraries Government Documents Department
Air transport by gliders : some technical observations

Air transport by gliders : some technical observations

Date: June 1, 1941
Creator: Stepniewski, Wieslaw
Description: This short analysis may be useful in determining the real tactical possibilities of "glider trains" and in adopting the course to be followed in possible studies of these questions. In this analysis most prominent are: (a) the power required for the train in level flight; (b) its speed; (c) climb; and (d) the type of airplane best suited for towing as well as design requirements for transport gliders.
Contributing Partner: UNT Libraries Government Documents Department
Air transport economics

Air transport economics

Date: October 1, 1922
Creator: Warner, Edward P
Description: The report presents a determination of air transport costs with and without subsidies.
Contributing Partner: UNT Libraries Government Documents Department
Air-water analogy and the study of hydraulic models

Air-water analogy and the study of hydraulic models

Date: July 1, 1953
Creator: Supino, Giulio
Description: The author first sets forth some observations about the theory of models. Then he established certain general criteria for the construction of dynamically similar models in water and in air, through reference to the perfect fluid equations and to the ones pertaining to viscous flow. It is, in addition, pointed out that there are more cases in which the analogy is possible than is commonly supposed.
Contributing Partner: UNT Libraries Government Documents Department
Airfoil measurements in the DVL high-speed wind tunnel (2.7-meter diameter)

Airfoil measurements in the DVL high-speed wind tunnel (2.7-meter diameter)

Date: June 1, 1949
Creator: Gothert, B
Description: Report is a brief summary of investigations on symmetrical and cambered airfoils in the DVL high-speed tunnel. Some information on the effects of low aspect ratio are also included.
Contributing Partner: UNT Libraries Government Documents Department
An airfoil spanning an open jet

An airfoil spanning an open jet

Date: September 1933
Creator: Stuper, J
Description: Proceeding from the fundamental problem on the mutual relation of a wing and free boundaries the distribution of the circulation is determined for an airfoil spanning an open jet of rectangular section at different aspect ratios, and then for an open jet of circular section. The solution is obtained by means of a Fourier series and computations have been performed for different values of the variables. The second part describes the experiments performed for the purpose of proving the theory. The results confirm the theory. In conclusion it defines the induced drag of a wing extending across an open jet and compares it with the drag of a monoplane having a span equal to the jet width at equal total lift.
Contributing Partner: UNT Libraries Government Documents Department
Airfoil Theory at Supersonic Speed

Airfoil Theory at Supersonic Speed

Date: June 1939
Creator: Schlichting, H
Description: A theory is developed for the airfoil of finite span at supersonic speed analogous to the Prandtl airfoil theory of 1918-1919 for incompressible flow. In addition to the profile and induced drags, account must be taken at supersonic flow of still another drag, namely, the wave drag, which is independent of the wing aspect ratio. Both wave and induced drags are proportional to the square of the lift and depend on the Mach number, that is, the ratio of flight to sound speed. In general, in the case of supersonic flow, the drag-lift ratio is considerably less favorable than is the case for incompressible flow. Among others the following examples are considered: 1) lifting line with constant lift distribution (horseshoe vortex); 2) computation of wave and induced drag and the twist of a trapezoidal wing of constant lift density; 3) computation of the lift distribution and drag of an untwisted rectangular wing.
Contributing Partner: UNT Libraries Government Documents Department
Airplane drag

Airplane drag

Date: December 1929
Creator: Topfer, Carl
Description: It has been less well understood that the induced drag (or, better said, the undesired increase in the induced drag as compared with the theoretical minimum calculated by Prandtl) plays a decisive role in the process of taking off and therefore in the requisite engine power. This paper seeks to clarify the induced drag.
Contributing Partner: UNT Libraries Government Documents Department
Airplane flight in the stratosphere

Airplane flight in the stratosphere

Date: February 1932
Creator: De Caria, Ugo
Description: This brief survey of the problems encountered in high-altitude flight deals in particular with the need for high lift coefficient in the wings, large aspect ratios in the wings, and also the problem of hermetically sealing the cabin.
Contributing Partner: UNT Libraries Government Documents Department
Airplane landing gear

Airplane landing gear

Date: July 1931
Creator: Maiorca, Salvatore
Description: This report presents an investigation of the design and construction of various types of landing gears. Some of the items discussed include: chassises, wheels, shock absorbers (rubber disk and rubber cord), as well as oleopneumatic shock absorbers. Various types of landing gears are also discussed such as the Messier, Bendix, Vickers, and Bleriot.
Contributing Partner: UNT Libraries Government Documents Department
Airplane parachutes

Airplane parachutes

Date: August 1925
Creator: Mazer,
Description: The "Bulletin Technique", of March, 1919, gave the results of tests and studies made up to that date in connection with airplane parachutes. This work has been continued.
Contributing Partner: UNT Libraries Government Documents Department
Airplane performance, past and present

Airplane performance, past and present

Date: December 1922
Creator: Warner, Edward P
Description: The progress of airplane performance, measured by speed, is recounted in this article.
Contributing Partner: UNT Libraries Government Documents Department
Airplane speeds of the future

Airplane speeds of the future

Date: January 1, 1923
Creator: Warner, Edward P
Description: While the reliability of predictions is poor the author still attempts to gauge the future speeds of airplanes.
Contributing Partner: UNT Libraries Government Documents Department
Airplane stability calculations and their verification by flight tests

Airplane stability calculations and their verification by flight tests

Date: July 1, 1922
Creator: Rota, Augusto
Description: For some time, the designers of airplanes have begun to occupy themselves with the question of longitudinal stability. In their quest to simplify calculation and data collection, the designers have attached the greatest importance to the coefficient of initial longitudinal stability. In this study a diagram was constructed from the data of the tunnel tests, which depends neither on the position of the center of gravity nor of the angle of deflection of the elevators. This diagram is constructed by means of straight lines drawn through the metacenters of the complete airplane, in a direction parallel to the tangents to the polar of the airplane relative to a system of axes fixed with reference to the airplane.
Contributing Partner: UNT Libraries Government Documents Department
Airplane stability in taxying

Airplane stability in taxying

Date: September 1, 1932
Creator: Anderlik, E
Description: The stability analysis of an airplane while rolling is much more simplified to the extent that it can be obtained for numerical data which can be put to practical use in the design of landing gear dimensions. Every landing gear type attains to a critical ground friction coefficient that decides the beginning of instability, i.e., nosing over. This study has, in addition, a certain interest for the use of wheel brakes.
Contributing Partner: UNT Libraries Government Documents Department
Airplane strength calculations and static tests in Russia : an attempt at standardization

Airplane strength calculations and static tests in Russia : an attempt at standardization

Date: September 1, 1928
Creator: unknown
Description: We are here giving a summary of the rules established by the Theoretical Section of the Central Aerodynamic Institute of Moscow for the different calculation cases of an airplane. It appears the engineers of the Aerodynamic Institute considered only thick or medium profiles. For these profiles they have attempted to increase the safety when the center of pressure moves appreciably toward the trailing edge.
Contributing Partner: UNT Libraries Government Documents Department
Airscrew Gyroscopic Moments

Airscrew Gyroscopic Moments

Date: September 1946
Creator: Bock, G.
Description: When flying in a turn or pulling out of a dive, the airscrew exerts a gyroscopic moment on the aircraft, In the case of airscrews with three or more blades, arranged symmetrically, the value of the gyroscopic moment is J(sub x) omega(sub x) omega(sub y), where J(sub x) denotes the axial moment of inertia about the axis of rotation of the airscrew, omega(sub x) the angular upeed of the airscrew about its axis, and omega (sub Y) the rotary speed of the whole aircraft about an axis parallel to the plane of the airscrew (e.g., when pulling up, the transverse axis of the aircraft). The gyroscopic moment then tends to rotate the aircraft about an axis perpendicular to those of the two angular speeds and, in the came of airscrews with three or more blades, is constant during a revolution of the airscrew. With two-bladed airscrews, on the contrary, although the calculate gyroscopic moment represents the mean value in time, it fluctuates about this value with a frequency equal to twice the revolutions per minute. In addition, pulsating moments likewise occur about the other two axes. This fact is known from the theory of the asymmetrical gyro; the calculations that ...
Contributing Partner: UNT Libraries Government Documents Department
Alloys similar to duralumin made in other countries than Germany

Alloys similar to duralumin made in other countries than Germany

Date: May 1925
Creator: Meissner, K L
Description: Attempts by other countries to develop patents for alloys similar to duralumin are presented. Duralumin is aluminum alloyed with 3.5-4.5% copper, 0.5% magnesium, and 0.25-1% of manganese.
Contributing Partner: UNT Libraries Government Documents Department
Altitude of equilibrium of an airship

Altitude of equilibrium of an airship

Date: March 1925
Creator: Nobile, Umberto
Description: This report details the procedure followed in establishing a general formula enabling the calculation of the maximum altitude attainable statically.
Contributing Partner: UNT Libraries Government Documents Department