Variation Of Boundary Layer Transition With Heat Transfer On Two Bodies Of Revolution At A Mach Number Of 312 PDF Download
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Author | : John R. Jack |
Publisher | : |
Total Pages | : 16 |
Release | : 1955 |
Genre | : Boundary layer |
ISBN | : |
Download Variation of Boundary-layer Transition with Heat Transfer on Two Bodies of Revolution at a Mach Number of 3.12 Book in PDF, ePub and Kindle
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.
Author | : N. S. Diaconis |
Publisher | : |
Total Pages | : 31 |
Release | : 1957 |
Genre | : Boundary layer |
ISBN | : |
Download Heat Transfer and Boundary-layer Transition on Two Blunt Bodies at Mach Number 3.12 Book in PDF, ePub and Kindle
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.
Author | : Richard J. Wisniewski |
Publisher | : |
Total Pages | : 20 |
Release | : 1960 |
Genre | : |
ISBN | : |
Download Correlation of Boundary-layer Transition Results on Highly Cooled Blunt Bodies Book in PDF, ePub and Kindle
Author | : K.R. Czarnecki |
Publisher | : |
Total Pages | : 11 |
Release | : 1955 |
Genre | : |
ISBN | : |
Download 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 Book in PDF, ePub and Kindle
Author | : Richard D. Samuels |
Publisher | : |
Total Pages | : 82 |
Release | : 1967 |
Genre | : Skim friction (Aerodynamics) |
ISBN | : |
Download Experimental Investigation of the Turbulent Boundary Layer at a Mach Number of 6 with Heat Transfer at High Reynolds Numbers Book in PDF, ePub and Kindle
Author | : J. Leith Potter |
Publisher | : |
Total Pages | : 128 |
Release | : 1965 |
Genre | : Boundary layer |
ISBN | : |
Download Boundary-layer Transition Under Hypersonic Conditions Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 25 |
Release | : 1954 |
Genre | : |
ISBN | : |
Download 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 Book in PDF, ePub and Kindle
Author | : |
Publisher | : |
Total Pages | : 792 |
Release | : 1971 |
Genre | : Aeronautics |
ISBN | : |
Download Scientific and Technical Aerospace Reports Book in PDF, ePub and Kindle
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 | : Louis S. Stivers |
Publisher | : |
Total Pages | : 32 |
Release | : 1960 |
Genre | : Airplanes |
ISBN | : |
Download 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 Book in PDF, ePub and Kindle
Author | : Robert J. Carros |
Publisher | : |
Total Pages | : 30 |
Release | : 1956 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Download 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 Book in PDF, ePub and Kindle
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.