Considerations on the Structure of Mixed Subsonic-supersonic Flow Patterns PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Considerations on the Structure of Mixed Subsonic-supersonic Flow Patterns PDF full book. Access full book title Considerations on the Structure of Mixed Subsonic-supersonic Flow Patterns by Karl Gottfried Guderley. Download full books in PDF and EPUB format.
Author: Karl Gottfried Guderley
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 100
Get Book Here
Book Description
Author: Karl Gottfried Guderley
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 100
Get Book Here
Book Description
Author: Gabi Ben-Dor
Publisher: Springer Science & Business Media
ISBN: 3540713824
Category : Science
Languages : en
Pages : 353
Get Book Here
Book Description
This book is a comprehensive state-of-the-knowledge summation of shock wave reflection phenomena from a phenomenological point of view. It includes a thorough introduction to oblique shock wave reflections, dealing with both regular and Mach types. It also covers in detail the corresponding two- and three-shock theories. The book moves on to describe reflection phenomena in a variety of flow types, as well as providing the resolution of the Neumann paradox.
Author: Karl Gottfried Guderley
Publisher:
ISBN:
Category : Diffusers
Languages : en
Pages : 22
Get Book Here
Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1026
Get Book Here
Book Description
Author: Zbigniew Krzywoblocki
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 218
Get Book Here
Book Description
Author: John R. Spreiter
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 94
Get Book Here
Book Description
Theoretical pressure distributions on nonlifting circular-arc airfoils in two-dimensional flows with high subsonic free-stream velocity are found by determining approximate solutions, through an iteration process, of an integral equation for transonic flow proposed by Oswatitsch. The integral equation stems directly from the small disturbance theory for transonic flow. This method of analysis possesses the advantage of remaining in the physical, rather than hodograph, variables and can be applied to airfoils having curved surfaces. After discussion of the derivation of the integral equation and qualitative aspects of the solution, results of calculations carried out for circular-arc airfoils in flows with free-stream Mach numbers up to unity are described.
Author: Robert V. Hess
Publisher:
ISBN:
Category : Gas dynamics
Languages : en
Pages : 72
Get Book Here
Book Description
This paper treats the interaction between hot layers extended along the wall and normal or oblique shocks moving over them. Emphasis is on the cases of large hot-layer temperatures and strong shock waves for which small-perturbation theories are not applicable. A variety of possible interaction patterns are described. Of greatest interest are the more extreme cases when the hot layer is forced to accumulate in a growing bubble-like region bound to the moving shock, and some of the cold air above the layer moves around the bubble and interposes a high-speed forward-moving cold jet between the wall and the bubble. For some cases, especially with oblique shocks, this reverse jet may not form. Mixing will eventually limit the size of the bubble and make its characteristics more nearly like those of the more familiar separation bubbles. The effects of viscosity at the wall remains essentially different, however, since the shock is moving relative to the wall.
Author: Donald H. Desy
Publisher:
ISBN:
Category : Bainitic steel
Languages : en
Pages : 898
Get Book Here
Book Description
Some of the factors believed to affect the strength and ductile-to-brittle transition temperature of bainitic steels, including mean ferrite path and degree of internal strain, have been studied. Strength was measured by diamond pyramid hardness, and transition temperature was obtained from a tensile impact test on small notched specimens. Seven laboratory heats of carbon-molybdenum steel and two heats of carbon steel were transformed isothermally to bainite at various temperatures and tested. Mean-ferrite-path measurements were made on electron micrographs of three of these steels. The mean ferrite path was found to have only a slight effect on the strength of bainite and no effect on the transition temperature. Preliminary measurements of X-ray line broadening indicate that the degree of internal strain may be the controlling factor in determining the strength of bainite. The transition temperatures of the bainites fell within a band between -80 and -160 degrees C and did not vary regularly with hardness, carbon or alloy content, or mean ferrite path. In the SAE 1062 steel at high strength levels, bainite has a transition temperature lower than that of tempered martensite at the same strength level.
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 512
Get Book Here
Book Description
Author: Arthur Earl Bryson
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 106
Get Book Here
Book Description
Interferometer measurements are given of the flow fields near two-dimensional wedge and circular-arc sections at zero angle of attack. Pressure distributions and drag coefficients as functions of Mach number were obtained and the wedge data are compared with theory. It is shown that the local Mach number at any point on the surface of a finite three dimensional body or an unswept two-dimensional body, moving through an infinite fluid, has a stationary value at Mach number 1 and, in fact, remains nearly constant for a range of speeds below and above Mach number 1. On the basis of this concept and the experimental data, pressure distributions and drag coefficients for the wedge and circular-arc sections are presented throughout the entire transonic range of velocities.
