A Systematic Investigation of Pressure Distributions at High Speeds Over Five Representative NACA Low-drag and Conventional Airfoil Sections PDF Download

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A Systematic Investigation of Pressure Distributions at High Speeds Over Five Representative NACA Low-drag and Conventional Airfoil Sections

A Systematic Investigation of Pressure Distributions at High Speeds Over Five Representative NACA Low-drag and Conventional Airfoil Sections PDF Author: Carl Kaplan
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 238

Book Description

A Systematic Investigation of Pressure Distributions at High Speeds Over Five Representative NACA Low-drag and Conventional Airfoil Sections

A Systematic Investigation of Pressure Distributions at High Speeds Over Five Representative NACA Low-drag and Conventional Airfoil Sections PDF Author: Carl Kaplan
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 238

Book Description

Annual Report - National Advisory Committee for Aeronautics

Annual Report - National Advisory Committee for Aeronautics PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages :

Book Description
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.

Report - National Advisory Committee for Aeronautics

Report - National Advisory Committee for Aeronautics PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 752

Book Description

Report

Report PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 76

Book Description

Axially Symmetric Shapes with Minimum Wave Drag

Axially Symmetric Shapes with Minimum Wave Drag PDF Author: Maxwell Alfred Heaslet
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 676

Book Description
The external wave drag of bodies of revolution moving at supersonic speeds can be expressed either in terms of the geometry of the body, or in terms of the body-simulating axial source distribution. For purposes of deriving optimum bodies under various given condtions, it is found that the second of the methods mentioned is the more tractable. By use of a quasi-cylindrical theory, that is, the boundary conditions are applied on the surface of a cylinder rather than on the body itself, the variational problems of the optimum bodies having prescribed volume or caliber are solved. The streamwise variations of cross-section area and drags of the bodies are exhibited, and some numerical results are given. The solutions are found to depend upon a single parameter involving Mach number and radius-lenght ration of the given cylinder. Variation of this parameter from zero to infinity gives the spectrum of optimum bodies with the given condition from the slender-body result of the two-dimensional. The numerical results show that for increasing values of the parameter, the optimum shapes quickly approach the two-dimensional.

Technical Note - National Advisory Committee for Aeronautics

Technical Note - National Advisory Committee for Aeronautics PDF Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 308

Book Description

Applied Mechanics Reviews

Applied Mechanics Reviews PDF Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 412

Book Description

NACA Research Memorandum

NACA Research Memorandum PDF Author:
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 64

Book Description

Experimental Investigation of a 90 Degree Cascade Diffusing Bend with an Area Ratio of 1.45:1 and with Several Inlet Boundary Layers

Experimental Investigation of a 90 Degree Cascade Diffusing Bend with an Area Ratio of 1.45:1 and with Several Inlet Boundary Layers PDF Author: Daniel Friedman
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 804

Book Description
An experimental investigation was conducted in order to determine the performance of a 90 degree cascade diffusing bend with an area ratio of 1.45:1 and a 19-inch square inlet with several inlet-boundary-layer shapes and thicknesses. The maximum mean inlet Mach number was 0.41 and the corresponding airfoil Reynolds number was 950,000. The experimental results seem to indicate that, when the duct configuration requires a bend, a certain amount of diffusion can be obtained without an appreciable rise in the total-pressure losses. If length is important, this configuration requires much less space than the usual diffuser-bend combination.

Aerodynamics of Wings and Bodies

Aerodynamics of Wings and Bodies PDF Author: Holt Ashley
Publisher: Courier Corporation
ISBN: 0486648990
Category : Technology & Engineering
Languages : en
Pages : 306

Book Description
This excellent, innovative reference offers a wealth of useful information and a solid background in the fundamentals of aerodynamics. Fluid mechanics, constant density inviscid flow, singular perturbation problems, viscosity, thin-wing and slender body theories, drag minimalization, and other essentials are addressed in a lively, literate manner and accompanied by diagrams.
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