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 Decade: 1950-1959
 Serial/Series Title: NACA Technical Memorandums
 Collection: Technical Report Archive and Image Library
Acoustics of a nonhomogeneous moving medium.

Acoustics of a nonhomogeneous moving medium.

Date: February 1, 1956
Creator: Blokhintsev, D I
Description: Theoretical basis of the acoustics of a moving nonhomogeneous medium is considered in this report. Experiments that illustrate or confirm some of the theoretical explanation or derivation of these acoustics are also included.
Contributing Partner: UNT Libraries Government Documents Department
Aerodynamic Forces on a Vibrating Unstaggered Cascade

Aerodynamic Forces on a Vibrating Unstaggered Cascade

Date: August 1, 1957
Creator: Soehngen, H.
Description: The unsteady aerodynamic forces, [based on two-dimensional incompressible flow considerations], are determined for an unstaggered cascade, the blades of which are vibrating in phase in an approach flow parallel to the blades.
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
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.
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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.
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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
Amplitude distribution and energy balance of small disturbances in plate flow

Amplitude distribution and energy balance of small disturbances in plate flow

Date: April 1, 1950
Creator: Schlichting, H
Description: The distribution of the correlation coefficient and of the amplitude of the disturbance velocities is calculated as a function of the distance from the wall for two neutral disturbances, one at the lower and one at the upper branch of the neutral stability curve. The energy balance of the disturbance motion is also investigated and it is found that as required for neutral stability the energy of the disturbance motion that is dissipated by viscosity is equal to the energy transferred to the disturbance motion from the main flow during one cycle.
Contributing Partner: UNT Libraries Government Documents Department
Analytical study of shimmy of airplane wheels

Analytical study of shimmy of airplane wheels

Date: September 1, 1952
Creator: Bourcier De Carbon, Christian
Description: The problem of shimmy of a castering wheel, such as the nose wheel of a tricycle gear airplane, is treated analytically. The flexibility of the tire is considered to be the primary cause of shimmy. The rather simple theory developed agrees rather well with previous experimental results. The author suggests that shimmy may be eliminated through a suitable choice of landing gear dimensions in lieu of a damper.
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Apparatus for measurements of time and space correlation

Apparatus for measurements of time and space correlation

Date: April 1, 1955
Creator: Favre, Alexandre; Gaviglio, J & Dumas, R
Description: A brief review is made of improvements to an experimental apparatus for time and space correlation designed for study of turbulence. Included is a description of the control of the measurements and a few particular applications.
Contributing Partner: UNT Libraries Government Documents Department
Application of the Method of Coordinate Perturbation to Unsteady Duct Flow

Application of the Method of Coordinate Perturbation to Unsteady Duct Flow

Date: September 1, 1958
Creator: Himmel, Seymour C.
Description: The method of coordinate perturbation is applied to the unsteady flow of a compressible fluid in ducts of variable cross section. Solutions, in the form of perturbation series, are obtained for unsteady flows in ducts for which the logarithmic derivative of area variation with respect to the space coordinate is a function of the 'smallness' parameter of the perturbation series. This technique is applied to the problem of the interaction of a disturbance and a shock wave in a diffuser flow. It is found that, for a special choice of the function describing the disturbance, the path of the shock wave can be expressed in closed form to first order. The method is then applied to the determination of the flow field behind a shock wave moving on a prescribed path in the x,t-plane. Perturbation series solutions for quite general paths are developed. The perturbation series solutions are compared with the more exact solutions obtained by the application of the method of characteristics. The approximate solutions are shown to be in reasonably accurate agreement with the solutions obtained by the method of characteristics.
Contributing Partner: UNT Libraries Government Documents Department
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