National Advisory Committee for Aeronautics (NACA) - 1,438 Matching Results

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Application of the Method of Coordinate Perturbation to Unsteady Duct Flow

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 i… more
Date: September 1958
Creator: Himmel, Seymour C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Effect of Free-Stream Turbulence on Heat Transfer From a Flat Plate

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, b… more
Date: September 1958
Creator: Sugawara, Sugao; Sato, Takashi; Komatsu, Hiroyasu & Osaka, Hiroichi
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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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

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.
Date: September 1958
Creator: Hansen, Arthur G.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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On the Flutter of Cylindrical Shells and Panels Moving in a Flow of Gas

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.
Date: September 1958
Creator: Stepanov, R. D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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Theory and Experiments on Supersonic Air-to-Air Ejectors

Description: A comparison of experiment with theory is made for air ejectors having cylindrical mixing sections and operating under conditions of supersonic primary flow and either mixed or supersonic regimes of mixing. The effect on ejector performance of such parameters as mixer length and cross section, terminating diffuser, primary Mach number, and primary nozzle position is presented in terms of mass flow and pressure ratio.
Date: September 1958
Creator: Fabri, J. & Paulon, J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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The Turbulent Boundary Layer on a Rough Curvilinear Surface

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 suffice… more
Date: September 1958
Creator: Droblenkov, V. F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Aerodynamic characteristics of the X-15/B-52 combination

Description: Report presenting an investigation to determine the carry loads and mutual aerodynamic interference effects from high-speed wind-tunnel tests and the drop characteristics of the X-15 through the B-52 flow field from low-speed dynamic-model drop tests and six-degree-of-freedom calculations. The X-15 installation was found to increase drag at cruise conditions by approximately 15 percent.
Date: 1959
Creator: Alford, William J., Jr. & Taylor, Robert T.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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