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 Serial/Series Title: NACA Technical Memorandums
 Collection: National Advisory Committee for Aeronautics Collection
Graphic Construction of Joukowski Wings

Graphic Construction of Joukowski Wings

Date: December 1, 1979
Creator: Trefftz, E.
Description: A plot of the cross sectional outline of a Joukowski wing is presented.
Contributing Partner: UNT Libraries Government Documents Department
Pressure Distribution on Joukowski Wings

Pressure Distribution on Joukowski Wings

Date: December 1, 1979
Creator: Blumenthal, O.
Description: The hydrodynamics and mathematical models as applied to the potential flow about a Joukowski wing are presented.
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.
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The effect of free-stream turbulence on heat transfer from a flat plate

The effect of free-stream turbulence on heat transfer from a flat plate

Date: September 1, 1958
Creator: Sugawara, Sugao; Sato, Takashi; Komatsu, Hiroyasu & Osaka, Hiroichi
Description: Turbulence was generated by using screens, and the turbulence percentage was measured by a hot-wire anemometer both in the boundary layer and the free stream. The local heat-transfer coefficient was measured at 12 locations along the plate for the cases of various turbulence levels. The transition Reynolds number from laminar to turbulent flow decreases as the main-stream turbulence level increases. In the range of laminar heat transfer the effect of turbulence in the main flow was not great, but in the range of turbulent heat transfer the heat-transfer coefficient increases according to the increase of turbulence.
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On Possible Similarity Solutions for Three-Dimensional Incompressible Laminar Boundary-Layer Flows Over Developable Surfaces and with Proportional Mainstream Velocity Components

On Possible Similarity Solutions for Three-Dimensional Incompressible Laminar Boundary-Layer Flows Over Developable Surfaces and with Proportional Mainstream Velocity Components

Date: September 1, 1958
Creator: Hansen, Arthur G.
Description: Analysis is presented on the possible similarity solutions of the three-dimensional, laminar, incompressible, boundary-layer equations referred to orthogonal, curvilinear coordinate systems. Requirements of the existence of similarity solutions are obtained for the following: flow over developable surface and flow over non-developable surfaces with proportional mainstream velocity components.
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On the Flutter of Cylindrical Shells and Panels Moving in a Flow of Gas

On the Flutter of Cylindrical Shells and Panels Moving in a Flow of Gas

Date: September 1, 1958
Creator: Stepanov, R. D.
Description: The equations of shells are taken in the form of the general technical theory of shallow shells and shells of medium length. The aerodynamic forces acting on a shell are taken into account only as forces of excess pressure according to the formula proposed by A.A. Iliushin in reference 3.
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The Turbulent Boundary Layer on a Rough Curvilinear Surface

The Turbulent Boundary Layer on a Rough Curvilinear Surface

Date: September 1, 1958
Creator: Droblenkov, V. F.
Description: A number of semiempirical approximate methods exist for determining the characteristics of the turbulent boundary layer on a curvilinear surface. At present, among these methods, the one proposed by L. G. Loitsianskii is given frequent practical application. This method is sufficiently effective and permits, in the case of wing profiles with technically smooth surfaces, calculating the basic characteristics of the boundary layer and the values of the overall drag with an accuracy which suffices for practical purposes. The idea of making use of the basic integral momentum equation ((d delta(sup xx))/dx) + ((V' delta(sup xx))/V) (2 + H) = (tau(sub 0))/(rho V(exp 2)) proves to be fruitful also for the solution of the problems in the determination of the characteristics of the turbulent boundary layer on a rough surface.
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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.
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Statistical Study of Turbulence: Spectral Functions and Correlation Coefficients

Statistical Study of Turbulence: Spectral Functions and Correlation Coefficients

Date: July 1, 1958
Creator: Frenkiel, Francois N.
Description: In reading the publications on turbulence of different authors, one often runs the risk of confusing the various correlation coefficients and turbulence spectra. We have made a point of defining, by appropriate concepts, the differences which exist between these functions. Besides, we introduce in the symbols a few new characteristics of turbulence. In the first chapter, we study some relations between the correlation coefficients and the different turbulence spectra. Certain relations are given by means of demonstrations which could be called intuitive rather than mathematical. In this way we demonstrate that the correlation coefficients between the simultaneous turbulent velocities at two points are identical, whether studied in Lagrange's or in Euler's systems. We then consider new spectra of turbulence, obtained by study of the simultaneous velocities along a straight line of given direction. We determine some relations between these spectra and the correlation coefficients. Examining the relation between the spectrum of the turbulence measured at a fixed point and the longitudinal-correlation curve given by G. I. Taylor, we find that this equation is exact only when the coefficient is very small.
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Elliptic Functions and Integrals with Real Modulus in Fluid Mechanics

Elliptic Functions and Integrals with Real Modulus in Fluid Mechanics

Date: June 1, 1958
Creator: Legendre, Robert
Description: Advantage of the elliptic functions and of the more general functions of Schwarz for fluid mechanics. Flows outside and inside polygons. Application to the calculation of an elbow diffuser for a wind tunnel. Properties of the elliptic integrals of the first kind and of the elliptic functions. Properties of the theta functions and decomposition of the elliptic functions into products of theta functions. Properties of the zeta functions. Decomposition of the elliptic functions into sums of zeta functions and calculations of the elliptic integrals. Applications to the calculation of wing profiles, of compressor profiles, and to the study of the vibrations of airplane wings and of compressor vanes. The manuscript of the present paper was checked by Mr. Eichelbrenner who corrected several imperfections and suggested numerous improvements to make reading of the paper easier. However, the limited subject does not permit filling in more than an incomplete knowledge of the properties of analytic functions.
Contributing Partner: UNT Libraries Government Documents Department
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