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**Partner:**UNT Libraries Government Documents Department

**Decade:**1950-1959

**Serial/Series Title:**NACA Technical Memorandums

**Collection:**National Advisory Committee for Aeronautics Collection

### 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.

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### 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.

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### 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.

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### 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

**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

**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.

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### 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.

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### 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

**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.

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### 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.

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### Basic Differential Equations in General Theory of Elastic Shells

**Date:**February 1, 1951

**Creator:**Vlasov, V. S.

**Description:**The shell shall be considered as a three-dimensional continuous medium; for the coordinate surface, the middle surface of the shell shall be assumed parallel to the bounding surfaces. Let alpha and beta be the curvilinear orthogonal coordinates of this surface, coinciding with the lines of principal curvatures, and gamma the distance along the normal from the point (alpha,beta) of the coordinate surface to any point (alpha,beta,gamma) of the shell.

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### Behavior of fast moving flow of compressible gas in cylindrical pipe in presence of cooling

**Date:**September 1, 1951

**Creator:**Varshavsky, G A

**Description:**For compressible flow with friction in a cylindrical pipe the momentum, continuity, and heat-transfer equations are examined to determine whether an increase in Mach number ("thermal" Laval nozzle) is obtainable through heat conduction from the gas through the pipe walls. The analysis is based on the assumption that the wall temperature is negligibly small in comparison with the stagnation temperature of the gas. The analysis leads to a negative result. When the gas cooling is increased by also considering radiation to the wall, a limited region at high temperatures is obtained where Mach number increases were theoretically possible. Obtaining this condition practically is considered impossible.

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### Boundary Layer

**Date:**May 1, 1956

**Creator:**Loitsianskii. L. G.

**Description:**The fundamental, practically the most important branch of the modern mechanics of a viscous fluid or a gas, is that branch which concerns itself with the study of the boundary layer. The presence of a boundary layer accounts for the origin of the resistance and lift force, the breakdown of the smooth flow about bodies, and other phenomena that are associated with the motion of a body in a real fluid. The concept of boundary layer was clearly formulated by the founder of aerodynamics, N. E. Joukowsky, in his well-known work "On the Form of Ships" published as early as 1890. In his book "Theoretical Foundations of Air Navigation," Joukowsky gave an account of the most important properties of the boundary layer and pointed out the part played by it in the production of the resistance of bodies to motion. The fundamental differential equations of the motion of a fluid in a laminar boundary layer were given by Prandtl in 1904; the first solutions of these equations date from 1907 to 1910. As regards the turbulent boundary layer, there does not exist even to this day any rigorous formulation of this problem because there is no closed system of equations ...

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### The Boundary Layers in Fluids with Little Friction

**Date:**February 1, 1950

**Creator:**Blasius, H.

**Description:**The vortices forming in flowing water behind solid bodies are not represented correctly by the solution of the potential theory nor by Helmholtz's jets. Potential theory is unable to satisfy the condition that the water adheres at the wetted bodies, and its solutions of the fundamental hydrodynamic equations are at variance with the observation that the flow separates from the body at a certain point and sends forth a highly turbulent boundary layer into the free flow. Helmholtz's theory attempts to imitate the latter effect in such a way that it joins two potential flows, jet and still water, nonanalytical along a stream curve. The admissibility of this method is based on the fact that, at zero pressure, which is to prevail at the cited stream curve, the connection of the fluid, and with it the effect of adjacent parts on each other, is canceled. In reality, however, the pressure at these boundaries is definitely not zero, but can even be varied arbitrarily. Besides, Helmholtz's theory with its potential flows does not satisfy the condition of adherence nor explain the origin of the vortices, for in all of these problems, the friction must be taken into account on principle, according ...

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### Calculation of the bending stresses in helicopter rotor blades

**Date:**March 1, 1951

**Creator:**De Guillenchmidt, P

**Description:**A comparatively rapid method is presented for determining theoretically the bending stresses of helicopter rotor blades in forward flight. The method is based on the analysis of the properties of a vibrating beam, and its uniqueness lies in the simple solution of the differential equation which governs the motion of the bent blades.

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### Calculation of the lateral-dynamic stability of aircraft

**Date:**February 1, 1952

**Creator:**Raikh, A

**Description:**Graphs and formulas are given with the aid of which all the aerodynamic coefficients required for computing the lateral dynamic stability can be determined. A number of numerical examples are given for obtaining the stability derivatives and solving the characteristic-stability equation. Approximate formulas are derived with the aid of which rapid preliminary computations may be made and the stability coefficients corrected for certain modifications of the airplane. A derivation of the lateral-dynamic-stability equations is included.

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### Calculation of the shape of a two-dimensional supersonic nozzle in closed form

**Date:**January 1, 1953

**Creator:**Cunsolo, Dante

**Description:**The idea is advanced of making a supersonic nozzle by producing one, two, or three successive turns of the whole flow; with the result that the wall contour can be calculated exactly by means of the Prandtl-Meyer "Lost Solution.".

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### Concerning the flow about ring-shaped cowlings of finite thickness Part I

**Date:**January 1, 1952

**Creator:**Kuchemann, Dietrich

**Description:**It is shown how one may obtain, in a simple manner, the forms of ring-shaped bodies from existing tables of functions according to the customary method of superposition of flow due to singularities and parallel flow. A number of examples of the forms and pressure distributions of annular source bodies with and without hub body are given, and the inlet conditions of such ring-shaped cowlings are investigated. Furthermore, the annular bodies of finite length are indicated that correspond to Joukowsky profiles for the two-dimensional case. The examples are to give a basis for the design of cross-sectional forms of ring-shaped cowlings and a survey of the flows to be expected.

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### Concerning the flow about ring-shaped cowlings Part II : annular bodies of infinite length with circulation for smooth entrance

**Date:**November 1, 1951

**Creator:**Kuchemann, Dietrich & Weber, Johanna

**Description:**The investigations carried out in a previous report (NACA TM 1325) concerning the flow about ring-shaped cowlings were extended by taking a circulation about the cowling into consideration. The present second report treats bodies of infinite length with approximately smooth entrance. The circulation was caused by distributing vortex rings of constant density over a stream surface extending to infinity. Furthermore, the influence of a hub body on such cowlings was dealt with. The examples treated are meant to give the designer a basis for his design.

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### Concerning the flow about ring-shaped cowlings Part IX : the influence of oblique oncoming flow on the incremental velocities and air forces at the front part of circular cowls

**Date:**February 1, 1952

**Creator:**Kuchemann, Dietrich & Weber, Johanna

**Description:**The dependence of the maximum incremental velocities and air forces on a circular cowling on the mass flow and the angle of attack of the oblique flow is determined with the aid of pressure-distribution measurements. The particular cowling tested had been partially investigated in NACA TM 1327.

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### Concerning the flow about ring-shaped cowlings Part VI : further measurements on inlet devices

**Date:**December 1, 1951

**Creator:**Kuchemann, Dietrich & Weber, Johanna

**Description:**The present report presents as a supplement to the fourth report (available as ATI 5045, Air Materiel Command) in the series of investigations concerning the flow about ring-shaped cowlings further wind-tunnel measurements on inlet devices which are to show the influence of the radius of the nose of the cowling on the flow conditions. Moreover, a simple rule for the design of such arrangements, containing a hub in the interior, is suggested.

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### Concerning the flow about ring-shaped cowlings Part VIII : further measurements on annular profiles

**Date:**February 1, 1952

**Creator:**Kuchemann, Dietrich & Weber, Johanna

**Description:**The measurements of part V (reference 1) of this series of reports, which concerned comparatively long ring profiles, are supplemented by measurements on shorter rings as they are used for shrouded propellers and cowlings of ring-shaped radiators. Mass-flow coefficients and profile drags are given. Furthermore, it has to be determined how far the potential theory describes the flow phenomenon with sufficient accuracy and whether the present theory for the calculation of thin annular profile yields useful profile forms and is suitable for determination of the mass flow for thick profiles.

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### Concerning the flow about ring-shaped cowlings XII : two new classes of circular cowls

**Date:**October 1, 1953

**Creator:**Kuchemann, Dietrich & Weber, Johanna

**Description:**For application in practice for annular radiator fairings and similar arrangements, two new classes of circular cowls are developed by theoretical method, and investigated in a systematic test series regarding their behavior under various working conditions.

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### Concerning the flow on ring-shaped cowlings XIII : the influence of a projecting hub

**Date:**October 1, 1953

**Creator:**Kuchemann, Dietrich

**Description:**The influence of thickness and length of a hub projecting from an inlet opening was investigated on one of the two new classes of circular cowls reported in NACA TM 1360.

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