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Variation Of Boundary Layer Transition With Heat Transfer On Two Bodies Of Revolution At A Mach Number Of 312
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Book Synopsis Variation of Boundary-layer Transition with Heat Transfer on Two Bodies of Revolution at a Mach Number of 3.12 by : John R. Jack
Download or read book Variation of Boundary-layer Transition with Heat Transfer on Two Bodies of Revolution at a Mach Number of 3.12 written by John R. Jack and published by . This book was released on 1955 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made at a Mach number of 3.12 to determine the effects of heat transfer on boundary-layer transition. Data were obtained for a cone cylinder and a parabolic-nosed cylinder at Reynolds numbers up to 12,000,000 based on body length. The results show that cooling the cone-cylinder model to a wall-to-free-stream static-temperature ratio of approximately 1.4 increased the transition Reynolds number from a value of about 2,000,000 at equilibrium to 10,600,000. For temperature ratios less than 1.4, the boundary-layer flow was laminar over the entire model. The rapid increase of transition Reynolds number with small reductions in temeprature ratio near 1.4 indicated that temperature ratios slight lower may result in a laminar boundary layer for very high Reynolds numbers. For the parabolic-nosed body, the transition Reynolds number was about twice that of the cone-cylinder model over the temperature range investigated.
Book Synopsis Heat Transfer and Boundary-layer Transition on Two Blunt Bodies at Mach Number 3.12 by : N. S. Diaconis
Download or read book Heat Transfer and Boundary-layer Transition on Two Blunt Bodies at Mach Number 3.12 written by N. S. Diaconis and published by . This book was released on 1957 with total page 31 pages. Available in PDF, EPUB and Kindle. Book excerpt: Local heat-transfer parameters were measured on a hemisphere-cone-cylinder and on a 120 degree-included-angle cone-cylinder at a free-stream Mach number of 3.12 and at free-stream unit Reynolds numbers as high as 1,292.000 per inch. Heat-transfer data are presented for the case of wall temperature approximat&ly equal to free-stream static temperature.
Book Synopsis Correlation of Boundary-layer Transition Results on Highly Cooled Blunt Bodies by : Richard J. Wisniewski
Download or read book Correlation of Boundary-layer Transition Results on Highly Cooled Blunt Bodies written by Richard J. Wisniewski and published by . This book was released on 1960 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis AN EXTENSION OF THE EFFECTS OF HEAT TRANSFER ON BOUNDARY-LAYER TRANSITION ON A PARABOLIC BODY OF REVOLUTION (NACA RM-10) AT A MACH NUMBER OF 1.61 by :
Download or read book AN EXTENSION OF THE EFFECTS OF HEAT TRANSFER ON BOUNDARY-LAYER TRANSITION ON A PARABOLIC BODY OF REVOLUTION (NACA RM-10) AT A MACH NUMBER OF 1.61 written by and published by . This book was released on 1954 with total page 25 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of the Turbulent Boundary Layer at a Mach Number of 6 with Heat Transfer at High Reynolds Numbers by : Richard D. Samuels
Download or read book Experimental Investigation of the Turbulent Boundary Layer at a Mach Number of 6 with Heat Transfer at High Reynolds Numbers written by Richard D. Samuels and published by . This book was released on 1967 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Boundary-layer Transition Under Hypersonic Conditions by : J. Leith Potter
Download or read book Boundary-layer Transition Under Hypersonic Conditions written by J. Leith Potter and published by . This book was released on 1965 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis An Investigation of the Effects of Heat Transfer on Boundary-layer Transition of a Parabilic Body of Revolution (NACA RM-10) at a Mach Number of 1.61 by : K.R. Czarnecki
Download or read book An Investigation of the Effects of Heat Transfer on Boundary-layer Transition of a Parabilic Body of Revolution (NACA RM-10) at a Mach Number of 1.61 written by K.R. Czarnecki and published by . This book was released on 1955 with total page 11 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1971 with total page 792 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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.
Book Synopsis Effects of Fixing Boundary-layer Transition for a Swept- and a Triangular-wing and Body Combination at Mach Numbers from 0.60 to 1.40 by : Louis S. Stivers
Download or read book Effects of Fixing Boundary-layer Transition for a Swept- and a Triangular-wing and Body Combination at Mach Numbers from 0.60 to 1.40 written by Louis S. Stivers and published by . This book was released on 1960 with total page 32 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 1948 with total page 770 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Mach Number on Boundary-layer Transition in the Presence of Pressure Rise and Surface Roughness on an Ogive-cylinder Body with Cold Wall Conditions by : Robert J. Carros
Download or read book Effect of Mach Number on Boundary-layer Transition in the Presence of Pressure Rise and Surface Roughness on an Ogive-cylinder Body with Cold Wall Conditions written by Robert J. Carros and published by . This book was released on 1956 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effect of Mach number variation from 1.8 to 7.4 on boundary-layer transition was investigated on a slender fin-stabilized ogive-cylinder body in free flight at a constant length Reynolds number of 13.8 million. The wall to free-stream temperature ratio was constant at a value of 1.0 below Mach number 4.5 and at a value of 1.8 above Mach number 4.5. Results of the test showed that increasing Mach number had a very favorable effect of increasing the extent of the laminar boundary layer for a given surface roughness. The transition data, when plotted as a function of a factor indicative of heat transfer, showed that heat transfer was possibly responsible for a good deal of the increase in transition Reynolds number with Mach number.
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 Boundary-layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6 by : Mitchel H. Bertram
Download or read book Boundary-layer Displacement Effects in Air at Mach Numbers of 6.8 and 9.6 written by Mitchel H. Bertram and published by . This book was released on 1959 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Controlled Surface Roughness on Boundary-layer Transition and Heat Transfer at Mach Numbers of 4.8 and 6.0 by : Paul F. Holloway
Download or read book Effect of Controlled Surface Roughness on Boundary-layer Transition and Heat Transfer at Mach Numbers of 4.8 and 6.0 written by Paul F. Holloway and published by . This book was released on 1964 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Mach Number, Leading Edge Bluntness and Sweep on Boundary-layer Transition on a Flat Plate by : Don W. Jillie
Download or read book Effects of Mach Number, Leading Edge Bluntness and Sweep on Boundary-layer Transition on a Flat Plate written by Don W. Jillie and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Foundations of Boundary Layer Theory for Momentum, Heat, and Mass Transfer by : Joseph A. Schetz
Download or read book Foundations of Boundary Layer Theory for Momentum, Heat, and Mass Transfer written by Joseph A. Schetz and published by Prentice Hall. This book was released on 1984 with total page 346 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aeronautical Engineering Review by :
Download or read book Aeronautical Engineering Review written by and published by . This book was released on 1957 with total page 1174 pages. Available in PDF, EPUB and Kindle. Book excerpt:
