Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Experimental Determination Of Aerodynamic Drag On A Blunted 10 Deg Cone At Angles Of Attack In Hypersonic Rarefied Flow PDF full book. Access full book title Experimental Determination Of Aerodynamic Drag On A Blunted 10 Deg Cone At Angles Of Attack In Hypersonic Rarefied Flow.
| Author | : David E. Boylan |
| Publisher | : |
| Total Pages | : 40 |
| Release | : 1964 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 2180 |
| Release | : 1964 |
| Genre | : |
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| Author | : |
| Publisher | : |
| Total Pages | : 1282 |
| Release | : 1982 |
| Genre | : Aeronautics |
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Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
| Author | : Peter F. Intrieri |
| Publisher | : |
| Total Pages | : 36 |
| Release | : 1966 |
| Genre | : Aerodynamic heating |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 914 |
| Release | : 1965 |
| Genre | : Science |
| ISBN | : |
| Author | : Marvin I. Kussoy |
| Publisher | : |
| Total Pages | : 20 |
| Release | : 1967 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 410 |
| Release | : 1987 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 31 |
| Release | : 1975 |
| Genre | : |
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A free-flying instrumented model was tested in a hypersonic facility at M = 5.30, 6.34 and 9.94 and Re = 300,000 to 1,200,000 ft. Aerodynamic lift, total drag and base drag coefficients were obtained together with detailed base pressure distribution measurements at angles of attack from 0 to 60 deg. The measured lift and drag coefficients showed good agreement with the modified Newtonian theory. The centerline base pressure/free-stream static pressure, psia distribution was nearly independent of the angle of attack from -10 to -30 deg but increased rapidly for all test conditions beyond alpha = -30 deg. For similar conditions at angle of attack and Reynolds number, an increase in Mach number resulted in an increase of the base pressure ratio. The measurements indicated a highly complex base flow region, and tentative explanation of the observed results was offered.
| Author | : |
| Publisher | : |
| Total Pages | : 988 |
| Release | : 1998 |
| Genre | : Aeronautics |
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| Author | : Donald Robert Crawford |
| Publisher | : |
| Total Pages | : 122 |
| Release | : 1965 |
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Drag coefficient data for hemispherically blunted 15 degree semi-angle cones were obtained experimentally for a Mach number of 5.8. The Reynolds number based on the model base diameter ranged from 550 to 3700 and the ratio of the wall temperature to the stagnation temperature varied from 0.07 to 0.94. The drag was found to increase linearly with increasing wall temperature with the bluntest cones being most sensitive to the change in wall temperature. The percentage drag increase over the experimental temperature range was at least 11%, and as much as 19%, for all models tested. At a constant wall temperature ratio the drag coefficient was linearly dependent on the 'hypersonic viscous parameter' with the value for the sharp cone being adequately predicted by second order boundary layer theory. With the wall temperature ratio and the hypersonic viscous parameter fixed the viscous drag coefficient for blunted cones was found to be relatively independent of the bluntness ratio. (Author).
