An Experimental Investigation of Hypersonic Flow Over Blunt Nosed Cones at a Mach Number of 5.8 PDF Download
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Author: Reginald M. Machell
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 0
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Author: Reginald M. Machell
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 0
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Author: Reginald M. Machell
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 106
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Author: William T. O'Bryant
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 0
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Author: William T O'Bryant
Publisher: Hassell Street Press
ISBN: 9781015061101
Category :
Languages : en
Pages : 146
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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.
Author: William T. O'Bryant
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 120
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Author: Reginald M. Machell
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Antonio Ferri
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 90
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Author: Raman Kalimuthu
Publisher: LAP Lambert Academic Publishing
ISBN: 9783848442560
Category :
Languages : en
Pages : 180
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Experimental studies were carried out to measure the aerodynamic forces in the presence of the spike attached to the blunt body for the length to diameter ratio of 0.5, 1.0, 1.5 and 2.0 and angle of attack up to 8 degree at Mach number 6. Five types of spikes, namely, conical, hemisphere, flat-face, hemisphere-disk and flat face-disk spikes were studied. The effect of conical and hemispherical spikes and flat faced-disk and a hemispherical-disk attached to a blunt nosed basic body has been investigated. The flow field was visualized with schlieren system. The coefficients of drag, lift and pitching moment were measured for different spike configurations using the six-component strain gauge balance. The influence of the spike shock wave generated from the spike which interacts with the reattachment shock was also investigated to understand the cause of drag reduction. Surface pressure distribution over the nose of the basic body was measured for all the cases of with and without spike at = 0 and 5 degree and Mach 6."
Author: Victor Zakkay
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 66
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Author: United States. Wright Air Development Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1246
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