Compressible Laminar Boundary Layer Over A Yawed Infinite Cylinder With Heat Transfer And Arbitrary Prandtl Number PDF Download

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Compressible Laminar Boundary Layer Over a Yawed Infinite Cylinder with Heat Transfer and Arbitrary Prandtl Number

Compressible Laminar Boundary Layer Over a Yawed Infinite Cylinder with Heat Transfer and Arbitrary Prandtl Number
Author: Eli Reshotko
Publisher:
Total Pages: 86
Release: 1957
Genre: Aerodynamic heating
ISBN:

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The equations for development of the compressible laminar boundary layer over a yawed infinite cylinder are presented. For compressible flow with a pressure gradient the chordwise and spanwise flows are not independent. By use of the Stewartson transformation and a linear viscosity-temperature relation, a set of three simultaneous ordinary differential equations is obtained in a form yielding similar solutions. These equations are solved for stagnation-line flow for surface temperatures from zero to twice the free-stream stagnation temperature and for a wide range of yaw angle and free-stream Mach number.


Similar Solutions for the Compressible Boundary Layer on a Yawed Cylinder with Transpiration Cooling

Similar Solutions for the Compressible Boundary Layer on a Yawed Cylinder with Transpiration Cooling
Author: Ivan E. Beckwith
Publisher:
Total Pages: 44
Release: 1959
Genre: Boundary layer
ISBN:

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Heat-transfer and skin-friction parameters obtained from exact solutions to the laminar compressible boundary-layer equations for infinite cylinders in yaw are presented. The effects of transpiration cooling, Prandtl number, pressure gradient, wall temperature, and viscosity relation were investigated. It is shown that as the Mach number is increased for a given large yaw angle the effects of pressure gradient become larger and the quantity of coolant required to maintain a given wall temperature is also increased. The use of a linear viscosity-temperature relation gives approximately the same results as the Sutherland viscosity-temperature relation except for very high aerodynamic heating rates.


NASA Technical Note

NASA Technical Note
Author:
Publisher:
Total Pages: 144
Release: 1975
Genre:
ISBN:

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Investigation of a Full-scale, Cascade-type Thrust Reverser

Investigation of a Full-scale, Cascade-type Thrust Reverser
Author: Robert C. Kohl
Publisher:
Total Pages: 728
Release: 1957
Genre: Cascades (Fluid dynamics)
ISBN:

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A double set of turning vanes was carried inside the jet tailpipe. To produce reverse thrust, the tailpipe opens into two side sections and the turning vanes move outward to form a V-shaped cascade, which deflects the exhaust-gas flow. Forward and reverse net thrust were measured over a range of engine speeds with the airplane stationary. Taxi tests were made to determine the comparative stopping distances using wheel braking and reverse thrust separately, and a combination of both. The effect of turning-vane spacing on thrust-reverser performance was determined by scale-model tests using unheated air.


Index of NACA Technical Publications

Index of NACA Technical Publications
Author: United States. National Advisory Committee for Aeronautics
Publisher:
Total Pages: 860
Release: 1957
Genre: Aeronautics
ISBN:

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Annual Report - National Advisory Committee for Aeronautics

Annual Report - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for Aeronautics
Publisher:
Total Pages:
Release: 1957
Genre: Aeronautics
ISBN:

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


Report

Report
Author:
Publisher:
Total Pages: 1138
Release: 1958
Genre: Aeronautics
ISBN:

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Sixth IUTAM Symposium on Laminar-Turbulent Transition

Sixth IUTAM Symposium on Laminar-Turbulent Transition
Author: Rama Govindarajan
Publisher: Springer Science & Business Media
Total Pages: 466
Release: 2006-01-18
Genre: Technology & Engineering
ISBN: 1402041594

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The dynamics of transition from laminar to turbulent flow remains to this day a major challenge in theoretical and applied mechanics. A series of IUTAM symposia held over the last twenty five years at well-known Centres of research in the subject - Novosibirsk, Stuttgart, Toulouse, Sendai and Sedona (Arizona) - has proved to be a great catalyst which has given a boost to research and our understanding of the field. At this point of time, the field is changing significantly with several emerging directions. The sixth IUTAM meeting in the series, which was held at the Jawaharlal Nehru Centre for Advanced Scientific Research, Bangalore, India, focused on the progress after the fifth meeting held at Sedona in 1999. The s- posium, which adhered to the IUTAM format of a single session, included seven invited lectures, fifty oral presentations and eight posters. During the course of the symposium, the following became evident. The area of laminar-turbulent transition has progressed considerably since 1999. Better theoretical tools, for handling nonlinearities as well as transient behaviour are now available. This is accompanied by an en- mous increase in the level of sophistication of both experiments and direct numerical simulations. The result has been that our understanding of the early stages of the transition process is now on much firmer footing and we are now able to study many aspects of the later stages of the transition process.