Turbulent Boundary-layer Temperature Recovery Factors in Two-dimensional Supersonic Flow

Turbulent Boundary-layer Temperature Recovery Factors in Two-dimensional Supersonic Flow PDF

Author: Maurice Tucker

Publisher:

Published: 1951

Total Pages: 30

ISBN-13:

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An analytical method is presented for obtaining turbulent temperature recovery factors for a thermally insulated surface in supersonic flow. The method is an extension of Squire's analysis for incompressible flow. The boundary layer velocity profile is represented by a power law and a similarity is postulated for squared-velocity the static-temperature-difference profiles.

Two-dimensional Flow on General Surfaces of Revolution in Turbomachines

Two-dimensional Flow on General Surfaces of Revolution in Turbomachines PDF

Author: John D. Stanitz

Publisher:

Published: 1952

Total Pages: 734

ISBN-13:

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A method of analysis is developed for two dimensional flow on general surfaces of revolution in turbomachines with arbitrary blade shapes. The method of analysis is developed for steady, compressible, nonviscous, irrotational flow that is assumed uniform normal to the surfaces of revolution. Incompressible solutions on a mean surface of revolution between the hub and shroud are presented for four rates through each of two centrifugal impellers with the same hub-shroud contours but with different blade spacings. In addition, correlation equations are developed whereby the velocity components and the stream function distribution can be predicted for compressible or incompressible flow in straight-blade impellers only, with any tip speed, flow rate, area variation, blade spacing, and for any flow surface of revolution.

Measurements of Upstream History Effects in Compressible Turbulent Boundary Layers

Measurements of Upstream History Effects in Compressible Turbulent Boundary Layers PDF

Author: David F. Gates

Publisher:

Published: 1973

Total Pages: 124

ISBN-13:

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The report describes an experimental study of compressible turbulent boundary layers for which the upstream history was systematically varied. A series of experiments was conducted using both a supersonic half nozzle and a conventional flat plate for which the nozzle throat and flat plate leading edge can be temperature controlled. The supersonic nozzle provided a favorable upstream pressure gradient together with a controlled thermal history at the throat. The flat plate provided upstream temperature control with no pressure history. Velocity and temperature profile and heat-transfer measurements were made in a downstream region of zero-pressure-gradient and constant wall temperature. (Modified author abstract).

Summary of Available Hail Literature and the Effect of Hail on Aircraft in Flight

Summary of Available Hail Literature and the Effect of Hail on Aircraft in Flight PDF

Author: Robert K. Souter

Publisher:

Published: 1952

Total Pages: 770

ISBN-13:

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Available information on the hail phenomenon affecting aircraft in flight has been examined. This paper attempts to coordinate the present knowledge of hail with the effect of hail on aircraft in flight and includes (1) a digest of the literature on the physical properties, the occurrence, and the formation of hai; (2) a survey of the hail effect on aircraft in flight from analyses of 57 cases of airplanes damaged by hail; (3) a resume of hail information for the benefit of pilots, forecasters, and ground operational personnel; (4) an annotated bibliography of 552 articles for use of research personnel.

Temperature Recovery Factors on a Slender 12° Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45°

Temperature Recovery Factors on a Slender 12° Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45° PDF

Author: John O. Reller

Publisher:

Published: 1955

Total Pages: 64

ISBN-13:

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Abstract: Temperature recovery factors were determined for a slender, thin-walled cone-cylinder, having a 12° vertex angle and a 1.25-inch-diameter cylinder, at Mach numbers from 3.02 to 6.30. The angle-of-attack range was 0° to 45° at Mach numbers up to 3.50, and about 0° to 20° at Mach numbers from 4.23 to 6.30. A transverse cylinder of the same diameter was also tested at Mach number 3.02. Free-stream Reynolds numbers varied from 1.8 to 11.0 million per foot. Flow visualization studies of boundary-layer transition and flow separation were made and the results correlated with recovery-factor measurements.

Turbulent Flow

Turbulent Flow PDF

Author: Galen Brandt Schubauer

Publisher: Princeton University Press

Published: 2015-12-08

Total Pages: 131

ISBN-13: 1400879582

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Part of the Princeton Aeronautical Paperback series designed to bring to students and research engineers outstanding portions of the twelve-volume High Speed Aerodynamics and Jet Propulsion series. These books have been prepared by direct reproduction of the text from the original series and no attempt has been made to provide introductory material or to eliminate cross reference to other portions of the original volumes. Originally published in 1945. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.

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