Download or read book The Influence of Low Wall Temperature on Boundary layer Transition and Local Heat Transfer on 2 inch diameter Hemispheres at a Mach Number of 4 95 and a Reynolds Number Per Foot of 73 2 X 106 written by Morton Cooper and published by . This book was released on 1960 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Influence of Low Wall Temperature on Boundary layer Transition and Local Heat Transfer on 2 inch diameter Hemispheres at a Mach Number of 4 95 and a Reynolds Number Per Foot of 73 2 X 106 written by Morton Cooper and published by . This book was released on 1960 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Influence of Low Wall Temperature on Boundary Layer Transition and Local Heat Transfer on 2 Inch Diameter Hemispheres at a Mach Number of 4 95 and a Reynolds Number Per Foot of 73 2 X 10 exp 6 written by Morton Cooper and published by . This book was released on 1960 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book Experimental Convective Heat Transfer to a 4 inch and 6 inch Hemisphere at Mach Numbers from 1 62 to 3 04 written by Leo T. Chauvin and published by . This book was released on 1954 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Equilibrium temperatures and heat-transfer coefficients for a hemispherical nose have been measured for Mach numbers from 1.62 to 3.04. Heat transfer to the surface of the hemisphere was presented as Stanton number against Reynolds number for various surface heating conditions. Heat transfer at the stagnation point has been measured and correlated with theory. Transition from a laminar to a turbulent boundary layer was obtained at Reynolds numbers of approximately 1 x 106 corresponding to a region on the body located between 45© and 60© from the stagnation point.
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:
Download or read book The Effect of Centrifugal Forces on Boundary Layer Transition for a Highly Heated Body written by Eugene Sevigny and published by . This book was released on 1959 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Temperature Recovery Factors on a Slender 12 Cone cylinder at Mach Numbers from 3 0 to 6 3 and Angles of Attack Up to 45 written by John O. Reller and published by . This book was released on 1955 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Temperature recovery factors were determined for a slender, thin-walled cone-cylinder, having a 12° vertex angle and a 1.25-inch-diameter cylinder, at Mach numbers from 3.02 to 6.30. The angle-of-attack range was 0° to 45° at Mach numbers up to 3.50, and about 0° to 20° at Mach numbers from 4.23 to 6.30. A transverse cylinder of the same diameter was also tested at Mach number 3.02. Free-stream Reynolds numbers varied from 1.8 to 11.0 million per foot. Flow visualization studies of boundary-layer transition and flow separation were made and the results correlated with recovery-factor measurements.
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.
Download or read book Turbulent boundary layer Heat transfer and Transition Measurements with Surface Cooling at Mach 6 written by Aubrey M. Cary and published by . This book was released on 1970 with total page 58 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Heat transfer Measurements at a Mach Number of 2 in the Turbulent Boundary Layer on a Flat Plate Having a Stepwise Temperature Distribution written by Raul Jorge Conti and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Local Aerodynamic Heat Transfer and Boundary layer Transition on Roughened Sphere ellipsoid Bodies at Mach Number 3 0 written by William D. Deveikis and published by . This book was released on 1961 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Heat transfer and Pressure Measurements on a Flat plate Surface and Heat transfer Measurements on Attached Protuberances in a Supersonic Turbulent Boundary Layer at Mach Numbers of 2 65 3 51 and 4 44 written by Paige B. Burbank and published by . This book was released on 1962 with total page 430 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The Effect of an Arbitrary Surface temperature Variation Along a Flat Plate on the Convective Heat Transfer in an Incompressible Turbulent Boundary Layer written by Morris W. Rubesin and published by . This book was released on 1951 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis was performed to determine the effects on the rates of convective heat transfer produced by arbitrary variations of the surface temperature with distance along a flat plate. The analysis was confined to the case of a low-speed turbulent boundary layer on a flat plate oriented parallel to the free-stream velocity. It was found that a continuously variable surface temperature has, in general, a smaller effect on the local convective heat transfer than does a surface-temperature discontinuity.
Download or read book Effect of Roughness on Heat Transfer to Hemisphere Cylinders at Mach Numbers 10 4 and 11 4 written by James C. Dunavant and published by . This book was released on 1967 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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:
Download or read book A Correlation of Heat transfer and Skin friction Data and an Experimental Reynolds Analogy Factor for Highly Cooled Turbulent Boundary Layers at Mach 5 0 written by Donald M. Wilson and published by . This book was released on 1969 with total page 82 pages. Available in PDF, EPUB and Kindle. Book excerpt: Turbulent boundary-layer heat transfer and skin-friction coefficients were measured on sharp slender cones at a free-stream Mach number of 5.0. Wall-to-stagnation temperature ratios from 0.15 to 0.80 were obtained by precooling or preheating the model. Tests were conducted for a wide range of Reynolds numbers by varying the tunnel supply pressure and temperature, thus providing data for naturally turbulent boundary layers. The experimental results were compared with existing theories which predict convective Stanton number or skin-friction coefficients. These comparisons indicate that the heat-transfer data are best predicted by the Spalding-Chi law and the skin friction by the Sommer-Short reference temperature method. The experimental Reynolds analogy factor is adequately predicted by Colburn's incompressible correlation for wall-to-stagnation temperature ratios above about 0.5. However, for lower wall temperature ratios, the experimental Reynolds analogy factor decreases with decreased temperature ratios in a manner which has not been previously reported. (Author).
