Heat Transfer on Unswept and 38 ̊swept Cylindrically Blunted Wedge Fins in Free Flight to Mach Number 4.11 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 Heat Transfer on Unswept and 38 ̊swept Cylindrically Blunted Wedge Fins in Free Flight to Mach Number 4.11 PDF full book. Access full book title Heat Transfer on Unswept and 38 ̊swept Cylindrically Blunted Wedge Fins in Free Flight to Mach Number 4.11 by Floyd G. Howard. Download full books in PDF and EPUB format.
Author: Floyd G. Howard
Publisher:
ISBN:
Category : Fins (Anatomy)
Languages : en
Pages : 56
Get Book Here
Book Description
Author: Floyd G. Howard
Publisher:
ISBN:
Category : Fins (Anatomy)
Languages : en
Pages : 56
Get Book Here
Book Description
Author: Floyd G. Howard
Publisher:
ISBN:
Category :
Languages : en
Pages : 48
Get Book Here
Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 42
Get Book Here
Book Description
Author: William M. Bland
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 36
Get Book Here
Book Description
Abstract: Four models of a thin magnesium fin, with the leading edge swept back 35°, have been tested in the preflight high-temperature jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va., at a Mach number of 2.0 for various stagnation temperatures between 2,310° and 3,500° R. This exploratory investigation was made to determine some effects of aerodynamic heating at high stagnation temperatures on the leading edges of fins and to determine the relative effectiveness of several leading-edge protective schemes.
Author:
Publisher:
ISBN:
Category : Grace at meals
Languages : en
Pages : 29
Get Book Here
Book Description
Author: Michael E. Tauber
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 44
Get Book Here
Book Description
Author: Langley Aeronautical Laboratory
Publisher: Hassell Street Press
ISBN: 9781015043015
Category :
Languages : en
Pages : 30
Get Book Here
Book Description
This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
![Free Flight Measurements of Pressure and Heat Transfer on a Blunt Leading-edge Caret Wing at Design and Off-design Mach Numbers (M [infinity] PDF](https://books.google.com/books/content/images/frontcover/dsY-PwAACAAJ?fife=w80-h100)
Author: G. H. Greenwood
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 45
Get Book Here
Book Description
Author: Franz von Reber
Publisher:
ISBN:
Category : Art, Ancient
Languages : en
Pages : 520
Get Book Here
Book Description
Author: Ernst Heinrich Hirschel
Publisher: Springer Science & Business Media
ISBN: 3540265198
Category : Technology & Engineering
Languages : en
Pages : 419
Get Book Here
Book Description
The last two decades have brought two important developments for aeroth- modynamics. One is that airbreathing hypersonic flight became the topic of technology programmes and extended system studies. The other is the emergence and maturing of the discrete numerical methods of aerodyn- ics/aerothermodynamics complementary to the ground-simulation facilities, with the parallel enormous growth of computer power. Airbreathing hypersonic flight vehicles are, in contrast to aeroassisted re-entry vehicles, drag sensitive. They have, further, highly integrated lift and propulsion systems. This means that viscous eflFects, like boundary-layer development, laminar-turbulent transition, to a certain degree also strong interaction phenomena, are much more important for such vehicles than for re-entry vehicles. This holds also for the thermal state of the surface and thermal surface effects, concerning viscous and thermo-chemical phenomena (more important for re-entry vehicles) at and near the wall. The discrete numerical methods of aerodynamics/aerothermodynamics permit now - what was twenty years ago not imaginable - the simulation of high speed flows past real flight vehicle configurations with thermo-chemical and viscous effects, the description of the latter being still handicapped by in sufficient flow-physics models. The benefits of numerical simulation for flight vehicle design are enormous: much improved aerodynamic shape definition and optimization, provision of accurate and reliable aerodynamic data, and highly accurate determination of thermal and mechanical loads. Truly mul- disciplinary design and optimization methods regarding the layout of thermal protection systems, all kinds of aero-servoelasticity problems of the airframe, et cetera, begin now to emerge.
