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Download Heat Transfer To A Hemispherically Blunted 9 Deg Half Angle Cone During Free Flight At Mach Numbers Up To 208 full books in PDF, epub, and Kindle. Read online Heat Transfer To A Hemispherically Blunted 9 Deg Half Angle Cone During Free Flight At Mach Numbers Up To 208 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Author :
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ISBN 13 :
Total Pages : 40 pages
Book Rating : 4.:/5 (317 download)
Download or read book Heat Transfer to a Hemispherically Blunted 9 Deg Half-angle Cone During Free Flight at Mach Numbers Up to 20.8 written by and published by . This book was released on 1963 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
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ISBN 13 :
Total Pages : 46 pages
Book Rating : 4.:/5 (317 download)
Download or read book Heat Transfer to a Hemispherically Blunted 9 Deg Half-angle Cone Cylinder at Hypersonic Free Flight Mach Numbers Up to 20.4 written by and published by . This book was released on 1964 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : David E. Boylan
Publisher :
ISBN 13 :
Total Pages : 68 pages
Book Rating : 4.3/5 (91 download)
Download or read book Laminar Heat Transfer on Sharp and Blunt Ten-degree Cones in Conical and Parallel Low-density Flow written by David E. Boylan and published by . This book was released on 1973 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents heat-transfer-rate measurements on sharp and blunt 10-deg half-angle cones at angles of attack between -9 and +10 deg in a low-density, hypersonic wind tunnel. Circumferential and longitudinal distributions are presented for cold wall conditions for a range at Mach and Reynolds numbers. The effect of source-like flows was studied by utilizing both conical and contoured expansion nozzles with the same free-stream similarity parameters and model wall temperatures. Comparisons are made with previously published experimental and theoretical results. (Author).
Author : Raul Jorge Conti
Publisher :
ISBN 13 :
Total Pages : 38 pages
Book Rating : 4.:/5 (31 download)
Download or read book Laminar Heat-transfer and Pressure Measurements at a Mach Number of 6 on a Sharp and Blunt 15° Half-angle Cones at Angles of Attack Up to 90° written by Raul Jorge Conti and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two circulation conical configurations having 15° half-angles were tested in laminar boundary layer at a Mach number of 6 and angles of attack up to 90°. One cone had a sharp nose and a fineness ratio of 1.87 and the other had a spherically blunted nose with a bluntness ratio of 0.1428 and a fineness ratio of 1.66. Pressure measurements and schlieren pictures of the flow showed that near-conical flow existed above 70° high pressure areas were present near the base and the bow shock wave was considerably curved.
Author : Peter F. Intrieri
Publisher :
ISBN 13 :
Total Pages : 40 pages
Book Rating : 4.:/5 (31 download)
Download or read book Free-flight Measurements of the Static and Dynamic Stability and Drag of a 10 Degree Blunted Cone at Mach Numbers 3.5 and 8.5 written by Peter F. Intrieri and published by . This book was released on 1962 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : David A. Stewart
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.:/5 (31 download)
Download or read book Convective Heat-transfer Rates on a Blunted 110° Cone with Hemispherical Afterbody at Hypersonic Speeds written by David A. Stewart and published by . This book was released on 1971 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : B. J. Griffith
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.3/5 (91 download)
Download or read book A Study of Laminar Heat Transfer to Spherically Blunted Cones and Hemisphere-cylinders at Hypersonic Conditions written by B. J. Griffith and published by . This book was released on 1963 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : J. David Dearing
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.:/5 (31 download)
Download or read book Laminar Heat-transfer Distributions for a Blunted-cone, Cone-frustum Reentry Configuration at Mach 10 written by J. David Dearing and published by . This book was released on 1969 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : CHARLES B. RUMSEY
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ISBN 13 :
Total Pages : 1 pages
Book Rating : 4.:/5 (227 download)
Download or read book Measurements of Aerodynamic Heat Transfer on a 15 Deg Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 written by CHARLES B. RUMSEY and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: Measurements of aerodynamic heat transfer were made at a number of stations along a cone-cylinder-flare model having a 15 degrees total-angle conical nose and a 10 degrees half-angle flare skirt. The maximum Mach number was 4.7, and local Reynolds numbers based on body length to a measurement station varied from 2 x 10 to the 6th power to 138 x 10 to the 6th power. Local Stanton numbers measured on the nose cone and flare showed fair agreement with laminar and turbulent theories, while the measurements on the cylinder were generally somewhat lower than theory. Experimental recovery factors, determined twice during the test, were unaccountably lower than theoretical values. Local transition Reynolds numbers, based on length from the nose tip, varied from 3 x 10 to the 6th power to 18 x 10 to the 6th power and were much lower than values previously obtained on the smoother nose of a similar model. At an angle of attack of about 9 degrees, the heat transfer on the flare increased to more than twie the theoretical turbulent value for zero angle of attack. (Author).
Author : Charles B. Rumsey
Publisher :
ISBN 13 :
Total Pages : 42 pages
Book Rating : 4.3/5 (126 download)
Download or read book Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10° Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 written by Charles B. Rumsey and published by . This book was released on 1956 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Aerodynamic heat-transfer measurements were at six stations on the 40-inch-long 10° total-angle conical nose of a rocket-propelled model which was flight tested at Mach numbers up to 5.9. The range of local Reynolds number was from 6.6 x 106 to 55.2 x 106. Laminar, transitional, and turbulent heat-transfer coefficients were measured, and, in general, the laminar and turbulent measurements were in good agreement with theory for cones. Experimental transition Reynolds numbers varied from less than 8.5 x 106 to 19.4 x 106. At a relatively constant ratio of wall temperature to local static temperature near 1.2, the transition Reynolds number increased from 9.2 x 106 to 19.4 x 106 as Mach number increased from 1.57 to 3.38. At Mach numbers near 3.7, the transition Reynolds number decreased as the skin temperature increased toward adiabatic wall temperatures.
Author : Charles R. Rumsey
Publisher :
ISBN 13 :
Total Pages : 66 pages
Book Rating : 4.:/5 (31 download)
Download or read book Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 written by Charles R. Rumsey and published by . This book was released on 1961 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Robert L. O'Neal
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.:/5 (31 download)
Download or read book Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 written by Robert L. O'Neal and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Charles B. Rumsey
Publisher :
ISBN 13 :
Total Pages : 26 pages
Book Rating : 4.3/5 (91 download)
Download or read book Free-flight Measurements of Aerodynamic Heat Transfer to Mach Number 3.9 and of Drag to Mach Number 6.9 of a Fin-stabilized Cone-cylinder Configuration written by Charles B. Rumsey and published by . This book was released on 1955 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic-heat-transfer measurements have been made at a station on the 10 degree total angle conical nose of a rocket-propelled model at flight Mach numbers of 1.4 to 3.9. The corresponding values of local Reynolds number varied from 18,000,000 to 46,000,000 and the ratio of skin temperature to local static temperature varied from 1.2 to 2.4. The experimental data, reduced to Stanton number, were in fair agreement with values predicted by Van Driest's theory for heat transfer on a cone with turbulent flow from the nose tip.
Author : Dennis M. Bushnell
Publisher :
ISBN 13 :
Total Pages : 40 pages
Book Rating : 4.:/5 (31 download)
Download or read book Heat-transfer and Pressure Distributions on Spherically Blunted 25 ̊half-angle Cone at Mach 8 and Angles of Attack Up to 90 ̊ written by Dennis M. Bushnell and published by . This book was released on 1968 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Charles B. Rumsey
Publisher :
ISBN 13 :
Total Pages : 50 pages
Book Rating : 4.3/5 (91 download)
Download or read book Heat-transfer Measurements in Free Flight at Mach Numbers Up to 14.6 on a Flat-faced Conical Nose with a Total Angle of 29© written by Charles B. Rumsey and published by . This book was released on 1958 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : James J. Buglia
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ISBN 13 :
Total Pages : 26 pages
Book Rating : 4.:/5 (155 download)
Download or read book Heat Transfer and Boundary-layer Transition on a Highly Polished Hemisphere-cone in Free Flight at Mach Numbers Up to 3.14 and Reynolds Numbers Up to 24 X 106 written by James J. Buglia and published by . This book was released on 1961 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A highly polished hemisphere-cone having a ratio of nose radius to base radius of 0.74 and a half-angle of 14.5 was flight tested at Mach numbers up to 4.70. Temperature and pressure data were obtained at Mach numbers up to 3.14 and a free-stream Reynolds number of 24 x 106 based on body diameter. The nose of the model had a surface roughness of 2 to 5 microinches as measured with an interferometer. The measured Stanton numbers were in good agreement with theory. Transition Reynolds numbers based on the laminar boundary-layer momentum thickness at transition ranged from 2,190 to 794. Comparison with results from previous tests of blunt shapes having a surface roughness of 20 to 40 microinches showed that the high degree of polish was instrumental in delaying the transition from laminar to turbulent flow.
Author :
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ISBN 13 :
Total Pages : 64 pages
Book Rating : 4.:/5 (317 download)
Download or read book Heating Rate Measurements Over 30 Deg and 40 Deg (half Angle) Blunt Cones in Air and Helium in the Langley Expansion Tube Facility written by and published by . This book was released on 1980 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: Convective heat-transfer measurements were made on the conical portion of spherically blunted cones (30 deg and 40 deg half angle) in the Langley expansion tube. The test gases used were helium and air: flow velocities were about 6.8 km/sec for helium and about 5.1 km/sec for air. The measured heating rates were compared with calculated results using a viscous shock-layer computer code. For air, various techniques to determine flow velocity yielded nearly identical results, but for helium the flow velocity varied by as much as 8% depending on which technique was used. The measured heating rates were in satisfactory agreement with calculation for helium test gas if the higher flow velocity was used, but for air and for helium assuming the lower flow velocity, the measurements were significantly greater than theory and the discrepancy increased with increasing distance along the cone.
