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Temperature Recovery Factors In The Transitional And Turbulent Boundary Layer On A 40 Degree Cone Cylinder At Mach Number 29
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Book Synopsis Temperature Recovery Factors in the Transitional and Turbulent Boundary Layer on a 40-Degree Cone Cylinder at Mach Number 2.9 by :
Download or read book Temperature Recovery Factors in the Transitional and Turbulent Boundary Layer on a 40-Degree Cone Cylinder at Mach Number 2.9 written by and published by . This book was released on 1953 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: Temperature recovery factors were determined on the cylindrical surface of a number of 40 deg cone cylinder models at zero angle of attack and at M = 2.86. The investigation was performed in a 40- by 40-cm intermittent tunnel and an 18- by 18-cm continous tunnel. With atmospheric tunnel-supply conditions, the turbulent recovery factor was found to be 0.89 + or - 0.5% and independent of Reynolds number in the range of 200,000 to 800,000, with Reynolds number based on wall conditions. The turbulent recovery factor can be represented by the cube root of the Prandtl number for a Prandtl number calculated at wall conditions. In the transitional region of the boundary layer, a maximum recovery factor 0.5 to 1% higher than the turbulent value was obtained. Boundary layer history had a marked effect on the value of the recovery factor. The results were compared with the theoretical and experimental findings of other investigators.
Book Synopsis Temperature Recovery Factors on a 40-Degree Cone Cylinder with Turbulent Boundary Layer at Mach Numbers 4.1 and 4.8 by :
Download or read book Temperature Recovery Factors on a 40-Degree Cone Cylinder with Turbulent Boundary Layer at Mach Numbers 4.1 and 4.8 written by and published by . This book was released on 1957 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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° by : John O. Reller
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.
Book Synopsis Measurements of Upstream History Effects in Compressible Turbulent Boundary Layers by : David F. Gates
Download or read book Measurements of Upstream History Effects in Compressible Turbulent Boundary Layers written by David F. Gates and published by . This book was released on 1973 with total page 124 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report describes an experimental study of compressible turbulent boundary layers for which the upstream history was systematically varied. A series of experiments was conducted using both a supersonic half nozzle and a conventional flat plate for which the nozzle throat and flat plate leading edge can be temperature controlled. The supersonic nozzle provided a favorable upstream pressure gradient together with a controlled thermal history at the throat. The flat plate provided upstream temperature control with no pressure history. Velocity and temperature profile and heat-transfer measurements were made in a downstream region of zero-pressure-gradient and constant wall temperature. (Modified author abstract).
Book Synopsis Temperature Recovery Factors on a 40-Degree Cone Cylinder with Turbulent Boundary Layer at Mach Numbers 4.1 and 4.8 by : S. M. Dmohoski
Download or read book Temperature Recovery Factors on a 40-Degree Cone Cylinder with Turbulent Boundary Layer at Mach Numbers 4.1 and 4.8 written by S. M. Dmohoski and published by . This book was released on 1957 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of the Turbulent-boundary-layer Temperature-recovery Factor on Bodies of Revolution at Mach Numbers from 2.0 to 3.8 by : Howard A. Stine
Download or read book Experimental Investigation of the Turbulent-boundary-layer Temperature-recovery Factor on Bodies of Revolution at Mach Numbers from 2.0 to 3.8 written by Howard A. Stine and published by . This book was released on 1952 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: A turbulent-boundary-layer temperature recovery factor f 0.885 plus or minus 0.011 was measured on both a 10 degree cone and a 40 degree cone cylinder at Mach numbers from 2 to 3.8 and Reynolds numbers based on surface kinematic viscosity from 400,000 to 4,000,000. Comparisons are made with available theories and experiments.
Book Synopsis Recovery Temperature Transition and Heat-transfer Measurements at Mach 5 by : Paul F. Brinich
Download or read book Recovery Temperature Transition and Heat-transfer Measurements at Mach 5 written by Paul F. Brinich and published by . This book was released on 1961 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Local Heat Transfer and Recovery Temperatures on a Yawed Cylinder at a Mach Number of 4.15 and High Reynolds Numbers by : Ivan E. Beckwith
Download or read book Local Heat Transfer and Recovery Temperatures on a Yawed Cylinder at a Mach Number of 4.15 and High Reynolds Numbers written by Ivan E. Beckwith and published by . This book was released on 1961 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Design studies of hypersonic lifting vehicles have generally indicated that aerodynamic heating may be reduced by using highly swept configurations with blunted leading edges. For laminar boundary layers the effect of sweep angle A on the heat transfer at the leading edge is usually taken as cos A as shown by the data of Feller (ref. 1) who measured the average heat transfer on the front half of a swept cylinder. More recent data (refs. 2 and 3) have indicated that the effect of sweep may be more nearly cos3/2 Lambda which, at a sweep angle of 75 deg, would result in a 50-percent reduction of the heat transfer predicted by the cos A variation. The data and theory of reference 4 also indicate a cos3/2 lambda variation but the theories of references 5 and 6 indicate a variation somewhere between cos A and cos3/2 lambda for large stream Mach numbers. The data of reference 7, in contrast to the investigations just cited, showed large increases in average heat transfer to a circular leading edge with increasing A up to a lambda of about 40 deg. These increases in heat transfer were probably caused by transition to turbulent flow which apparently resulted primarily from the inherent instability of the three-dimensional boundary layer flow on a yawed cylinder. The leading-edge Reynolds numbers of reference 7 were considerably larger than the values in references 1 to 4 and were also larger than typical values for full-scale leading edges of hypersonic vehicles; hence, the main application of the high Reynolds number tests will probably be to bodies at angle of attack.
Book Synopsis Laminar, Transitional, and Turbulent Heat Transfer to a Cone-cylinder-flare Body at Mach 8.0 by : Victor Zakkay
Download or read book Laminar, Transitional, and Turbulent Heat Transfer to a Cone-cylinder-flare Body at Mach 8.0 written by Victor Zakkay and published by . This book was released on 1962 with total page 86 pages. Available in PDF, EPUB and Kindle. Book excerpt: A modified equation for the heat transfer coefficient in the transitional and fully turbulent region based on the F.P.R.E. method is then presented. This method gives good agreement with the experimental results presented here.
Book Synopsis Measurements of Pressure and Local Heat Transfer on a 20° Cone at Angles of Attack Up to 20° for a Mach Number of 4.95 by : Jerome D. Julius
Download or read book Measurements of Pressure and Local Heat Transfer on a 20° Cone at Angles of Attack Up to 20° for a Mach Number of 4.95 written by Jerome D. Julius and published by . This book was released on 1959 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Boundary Layer Temperature Recovery Factor on a Cone at Nominal Mach Number Six by : Douglas S. Mackay
Download or read book Boundary Layer Temperature Recovery Factor on a Cone at Nominal Mach Number Six written by Douglas S. Mackay and published by . This book was released on 1953 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effects of Mach Number and Wall-temperature Ratio on Turbulent Heat Transfer at Mach Numbers from 3 to 5 by : Thorval Tendeland
Download or read book Effects of Mach Number and Wall-temperature Ratio on Turbulent Heat Transfer at Mach Numbers from 3 to 5 written by Thorval Tendeland and published by . This book was released on 1959 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: The heat-transfer data obtained from the model were found to correlate when the T' method of Sommer and Short was used. The increase in turbulent heat-transfer rate with a reduction in wall to free-stream temperature ratio was of the same order of magnitude as has been found for the turbulent skin-friction coefficient.
Book Synopsis Measurements of Aerodynamic Heat Transfer in Turbulent Separated Regions at a Mach Number of 1.8 by : Benjamine J. Garland
Download or read book Measurements of Aerodynamic Heat Transfer in Turbulent Separated Regions at a Mach Number of 1.8 written by Benjamine J. Garland and published by . This book was released on 1958 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Temperature Recovery Factors on a Slender 12 Degree Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45 Degrees by : John O. Jr Reller
Download or read book Temperature Recovery Factors on a Slender 12 Degree Cone-cylinder at Mach Numbers from 3.0 to 6.3 and Angles of Attack Up to 45 Degrees written by John O. Jr Reller and published by . This book was released on 1955 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer on a 15 Degree Cone-cylinder-flare Configuration in Free Flight at Mach Numbers Up to 4.7 by : Charles R. Rumsey
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:
Download or read book Sci-tech Book Profiles written by and published by . This book was released on 1965 with total page 856 pages. Available in PDF, EPUB and Kindle. Book excerpt: Includes title page, table of contents, list of contributors, preface and all indexes of each book.
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.
