Masters Theses in the Pure and Applied Sciences

Masters Theses in the Pure and Applied Sciences

Author: Wade H. Shafer

Publisher: Springer Science & Business Media

Published: 2013-11-21

Total Pages: 307

ISBN-13: 1475757794

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Masters Theses in the Pure and Applied Sciences was first conceived, published, and dis· seminated by the Center for Information and Numerical Data Analysis and Synthesis (CINDAS) *at Purdue University in 1957, starting its coverage of theses with the academic year 1955. Beginning with Volume 13, the printing and dissemination phases of the ac· tivity were transferred to University Microfilms/Xerox of Ann Arbor, Michigan, with the thought that such an arrangement would be more beneficial to the academic and general scientific and technical community. After five years of this joint undertaking we had concluded that it was in the interest of all concerned if the printing and distribution of the volume were handled by an international publishing house to assure improved service and broader dissemination. Hence, starting with Volume 18, Masters Theses in the Pure and Applied Sciences has been disseminated on a worldwide basis by Plenum Publishing Corporation of New York, and in the same year the coverage was broadened to include Canadian universities. All back issues can also be ordered from Plenum. We have reported in Volume 20 (thesis year 1975) a total of 10,374 theses titles from 28 Canadian and 239 United States universities. We are sure that this broader base for theses titles reported will greatly enhance the value of this important annual reference work. The organization of Volume 20 is identical to that of past years. It consists of theses titles arranged by discipline and by university within each discipline.


Experimental Investigation of Flutter of a Propeller with Clark Y Section Operating at Zero Forward Velocity at Positive and Negative Blade-angle Settings

Experimental Investigation of Flutter of a Propeller with Clark Y Section Operating at Zero Forward Velocity at Positive and Negative Blade-angle Settings

Author: John E. Baker

Publisher:

Published: 1949

Total Pages: 686

ISBN-13:

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The highest flutter speeds were found in the vicinity of the angle of zero aerodynamic moment and the flutter speed increased considerably in this region with decreasing pressure. Over the rest of the pitch range, the flutter speeds were much lower and varied little with pressure.


Experimental Investigation of Temperature Recovery Factors on Bodies of Revolution at Supersonic Speeds

Experimental Investigation of Temperature Recovery Factors on Bodies of Revolution at Supersonic Speeds

Author: William R. Wimbrow

Publisher:

Published: 1949

Total Pages: 26

ISBN-13:

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Local temperature recovery factors have been measured on two bodies of revolution at Mach numbers of 2.0 and are shown to be independent of Mach number, Reynolds number, or body shape. The measured recovery factor is well represented by the square root of Prandtl number for laminar boundary layers and by the cube root of Prandtl number for turbulent boundary layers, as predicted by theory.


Experimental Investigation of the Effects of Viscosity on the Drag of Bodies of Revolution at a Mach Number of 1.5

Experimental Investigation of the Effects of Viscosity on the Drag of Bodies of Revolution at a Mach Number of 1.5

Author: Dean R. Chapman

Publisher:

Published: 1947

Total Pages: 92

ISBN-13:

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Summary: Tests were conducted to determine the effects of viscosity on the drag and base pressure characteristics of various bodies of revolution at a Mach number of 1.5. The models were tested both with smooth surfaces and with roughness added to evaluate the effects of Reynolds number for both laminar and turbulent boundary layers. The principal geometric variables investigated were after-body shape and length-diameter ratio. For most models, force tests and base pressure measurements were made over a range of Reynolds numbers, based on model length, from 0.6 million to 5.0 millions. Schlieren photographs were used to analyze the effects of viscosity on flow separation and shock-wave configuration near the base and to verify the condition of the boundary layer as deduced from force tests. The results are discussed and compared with theoretical calculations.