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Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1498
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1498
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 552
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Book Description
Author: Gerald W. Braun
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 254
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Book Description
Wind tunnel tests were performed which simulated the flow pulsations which are sometimes produced in engine inlets by shock-boundary layer interaction. Shock Mach numbers from 1.2 to 1.4 were used and the boundary layer was influenced by air bleeding in or sucking off. The flow was observed by shodowgraph and static and total pressures were measured by means of low frequency and high frequency response instruments. Static wall pressures, boundary layer pressure profiles, and total pressure distributions across several tunnel cross sections were plotted. The data were analyzed with respect to their rms value and power spectral density. A literature survey and an analytical investigation of the pulsations in a diffuser with nonviscous flow are included. (Author).
Author: United States. Wright Air Development Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1246
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Book Description
Author: Eugene S. Love
Publisher:
ISBN:
Category : Aerodynamic load
Languages : en
Pages : 702
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Book Description
Some recent contributions to the problem of shock-induced separation of the boundary layer are examined, and additional analytical and experimental results are presented. The probable ranges of pressure rises and flow deflections associated with separation are indicated. Consideration is given to the effects of Mach number, adverse pressure gradient, and Reynolds number for laminar boundary layers and to the effects of Mach number, Reynolds number, and ratio of sepcific heats for turbulent boundary layers.
Author: Heinrich Görtler
Publisher: Springer Science & Business Media
ISBN: 3642458858
Category : Technology & Engineering
Languages : en
Pages : 423
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Book Description
Der BeschluB des Generalrats der Internationalen Union fill Theo retische und Angewandte Mechanik (IUTAM), ein Symposium tiber Grenzschichtforschung vorzubereiten, war von dem Wunsch getragen, Wissenschaftlern aus aller Welt, die in eigenen Arbeiten zu den neueren Fortschritten auf diesem wichtigen Gebiet der Stromungsmechanik wesentlich beigetragen haben, zu grtindlichen Diskussionen Gelegenheit zu geben. Die grundsatzlichen Probleme der Grenzschichtforschung soUten bei der Aussprache im V ordergrund stehen, die technischen An wendungen muBten im Hintergrund bleiben. Da eine echte Diskussion nur in einem relativ kleinen Kreis moglich ist, hat das Wissenschaftliche Komitee den Kreis der Teilnehmer be schrankt, dabei aber nach Moglichkeit Vertreter aus allen an den Fort schritten der Grenzschichtforschung beteiligten Nationen zusammenge fUhrt. Die Teilnehmer wurden in Beratungen des Wissenschaftlichen Komitees ausgewahlt und entweder zur Erstattung eines allgemeinen oder eines speziellen Berichtes eingeladen bzw. zur Teilnahme an den Diskussionsveranstaltungen aufgefordert. Das Ergebnis dieser Tagung legen wir hiermit vor. 1m Druck sind aIle jene Fragen und Bemerkungen aus den Diskussionen weggelassen wor den, die sich durch das V orliegen des voUen V ortragstextes in diesem Buch von selbst erledigen, bzw. die durch nachtragliche Bearbeitung des Manuskriptes von den Autoren beriicksichtigt worden sind. Wir empfinden es mit Dank als eine Ehrung, daB die erste Veranstal tung der IUTAM in Deutschland die Grenzschichtforschung behandelt und damit das Gedenken an LUDWIG PRANDTL wachhalt, den Begriinder der Grenzschichtforschung und den Forderer der modernen Stromungs forschung.
Author: Ernst Heinrich Hirschel
Publisher: Springer Science & Business Media
ISBN: 354089974X
Category : Technology & Engineering
Languages : en
Pages : 512
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Book Description
In this book selected aerothermodynamic design problems in hypersonic vehicles are treated. Where applicable, it emphasizes the fact that outer surfaces of hypersonic vehicles primarily are radiation-cooled, an interdisciplinary topic with many implications.
Author:
Publisher: Academic Press
ISBN: 0080575609
Category : Science
Languages : en
Pages : 591
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Book Description
Advances in Heat Transfer
Author: W. Fiszdon
Publisher: Elsevier
ISBN: 1483149307
Category : Technology & Engineering
Languages : en
Pages : 398
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Book Description
Fluid Dynamics Transactions, Volume 1 is a compilation of papers presented at the Fifth Symposium on Fluid Dynamics held in Poland from August 26 to September 2, 1961. The symposium provided a forum for discussing developments in fluid dynamics based on the following topics: mathematical methods, hypersonic flow, rarefied gas dynamics, and magnetohydrodynamics. This volume is comprised of 26 chapters and begins by presenting equations for gas dynamics and highlighting some of applications of the general results. The discussion then turns to Cauchy's problem for the compressible flow of the simple wave type; the use of exact numerical methods for the solution of boundary layer problems; and the effect of surface catalytic efficiency on stagnation point heat transfer. A geometric method of classifying solutions of gas dynamics using certain space and the time-space Lie transformation groups is described. Subsequent chapters explore supersonic flow past blunt bodies; application of the Monte Carlo method to the analysis of rarefied gas flows; and fluid-fluid displacement in a porous medium. This book will be a useful resource for engineers and other scientists interested in fluid dynamics.
Author: Herbert S. Ribner
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 738
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Book Description
The interaction of a convected field of turbulence with a shock wave has been analyzed to yield the modified turbulence, entropy spotiness, and noise generated downstream of the shock. This analysis generalizes the results of Technical Note 2864, which apply to a single spectrum component, to give the shock-interaction effects of a complete turbulence field. The previous report solved the basic gas-dynamic problem, and the present report has added the necessary spectrum analysis.
