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Experimental Convective Heat Transfer To A 4 Inch And 6 Inch Hemisphere At Mach Numbers From 162 To 304
Download Experimental Convective Heat Transfer To A 4 Inch And 6 Inch Hemisphere At Mach Numbers From 162 To 304 full books in PDF, epub, and Kindle. Read online Experimental Convective Heat Transfer To A 4 Inch And 6 Inch Hemisphere At Mach Numbers From 162 To 304 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Preliminary Results from a Free-flight Investigation of Boundary-layer Transition and Heat Transfer on a Highly Polished 8-inch-diameter Hemisphere-cylinder at Mach Numbers Up to 3 and Reynolds Numbers Based on a Length of 1 Foot Up to 17.7 X 106 by : James R. Hall
Download or read book Preliminary Results from a Free-flight Investigation of Boundary-layer Transition and Heat Transfer on a Highly Polished 8-inch-diameter Hemisphere-cylinder at Mach Numbers Up to 3 and Reynolds Numbers Based on a Length of 1 Foot Up to 17.7 X 106 written by James R. Hall and published by . This book was released on 1957 with total page 34 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8 by : Davis H. Crawford
Download or read book Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8 written by Davis H. Crawford and published by . This book was released on 1956 with total page 680 pages. Available in PDF, EPUB and Kindle. Book excerpt: At the stagnation point, the theory of Sibulkin, using the diameter and conditions behind the normal shock, was in good agreement with the experiment when the velocity graident at the stagnation opint appropriate to the free-stream Mach number was used.
Book Synopsis Experimental Investigation of Heat-transfer Distributions in Deep Cavities in Hypersonic Separated Flow by : Allan R. Wieting
Download or read book Experimental Investigation of Heat-transfer Distributions in Deep Cavities in Hypersonic Separated Flow written by Allan R. Wieting and published by . This book was released on 1970 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Hypervelocity wind tunnel tests to determine local cold wall convective heating rates to small rectangular cavities,
Book Synopsis An Experimental and Numerical Study of Steady Forced-convection Heat Transfer in a Spherical Annulus by : Dean Byard Tuft
Download or read book An Experimental and Numerical Study of Steady Forced-convection Heat Transfer in a Spherical Annulus written by Dean Byard Tuft and published by . This book was released on 1980 with total page 242 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10° Cone in Free Flight at Supersonic Mach Numbers Up to 5.9 by : Charles B. Rumsey
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.
Book Synopsis Variation in Heat Transfer During Transient Heation of a Hemisphere at a Mach Numer of 2 by : Roland D. English
Download or read book Variation in Heat Transfer During Transient Heation of a Hemisphere at a Mach Numer of 2 written by Roland D. English and published by . This book was released on 1960 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of Free-convection Heat Transfer in Vertical Tube at Large Grashof Numbers by : E. R. G. Eckert
Download or read book Experimental Investigation of Free-convection Heat Transfer in Vertical Tube at Large Grashof Numbers written by E. R. G. Eckert and published by . This book was released on 1952 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Review of High-speed, Convective, Heat-transfer Computation Methods by : Michael E. Tauber
Download or read book A Review of High-speed, Convective, Heat-transfer Computation Methods written by Michael E. Tauber and published by . This book was released on 1989 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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 by : Charles B. Rumsey
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.
Book Synopsis Heat-transfer and Pressure Distributions on Hemisphere-cylinders in Methane-air Combustion Products at Mach 7 by : Irving Weinstein
Download or read book Heat-transfer and Pressure Distributions on Hemisphere-cylinders in Methane-air Combustion Products at Mach 7 written by Irving Weinstein and published by . This book was released on 1973 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer and pressure distributions were measured over the surfaces of three hemisphere-cylinder models tested at a nominal Mach number of 7 in the Langley 8-foot high-temperature structures tunnel which uses methane-air products of combustion as a test medium. The results showed that the heat-transfer and pressure distributions over the surface of the models were in good agreement with experimental data obtained in air and also with theoretical predictions.
Book Synopsis Heat Transfer to the Conical Afterbody of a Blunt-nosed Reentry Body with Various Nose-edge Radii at Mach 6 by :
Download or read book Heat Transfer to the Conical Afterbody of a Blunt-nosed Reentry Body with Various Nose-edge Radii at Mach 6 written by and published by . This book was released on 1965 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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 (10)6 by : James J. Buglia
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 (10)6 written by James J. Buglia and published by . This book was released on 1957 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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 by : James J. Buglia
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.
Book Synopsis Laminar Heat Transfer Characteristics of a Hemisphere for the Mach Number Range 1.9 to 4.9 by : Irving Korobkin
Download or read book Laminar Heat Transfer Characteristics of a Hemisphere for the Mach Number Range 1.9 to 4.9 written by Irving Korobkin and published by . This book was released on 1954 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1988 with total page 384 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Heat Transfer and Boundary-layer Transition on an 8-inch-diameter Hemisphere-cylinder in Free Flight for a Mach Number Range of 2.00 to 3.88 by : Benjamine J. Garland
Download or read book Measurements of Heat Transfer and Boundary-layer Transition on an 8-inch-diameter Hemisphere-cylinder in Free Flight for a Mach Number Range of 2.00 to 3.88 written by Benjamine J. Garland and published by . This book was released on 1957 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
