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 Heat transfer Measurements on a Flat Plate and Attached Protuberances in a Turbulent Boundary Layer at Mach Numbers of 2 65 3 51 and 4 44 written by Robert L. Stallings and published by . This book was released on 1964 with total page 246 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Heat transfer on a Flat Plate with Attached Protuberances in a Turbulant Boundary Layer at Mach Number of 2 49 3 51 and 4 44 written by Lana Murphy Couch and published by . This book was released on 1966 with total page 110 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 0 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 J. Conti and published by . This book was released on 1959 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Heat transfer Measurements on a Flat Plate and Attached Fins at Mach Numbers of 3 51 and 4 44 written by Earl A. Price and published by . This book was released on 1964 with total page 46 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 423 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 Heat transfer and Pressure Measurements on a Flat plate Surface and Heat transfer Measurement on Attaches 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 423 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Heat transfer Measurements on a Flat Plate with Attached Protuberances in a Turbulent Boundary Layer at Mach Numbers of 2 49 3 51 and 4 44 written by Lana Murphy Couch and published by . This book was released on 1966 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Pressures and Turbulent Heat transfer Coefficients Associated with Sinusoidal Protuberances on a Flat Plate at a Mach Number of 3 written by Charles P. Shore and published by . This book was released on 1963 with total page 40 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 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.
Download or read book Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1 90 to 3 07 written by Robert L. O'Neal and published by . This book was released on 1962 with total page 44 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 An Investigation of Heat Transfer Within Regions of Separated Flow at a Mach Number of 6 0 written by Paul F. Holloway and published by . This book was released on 1965 with total page 106 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Heat Mass and Momentum Transfer for Flow Over a Flat Plate with Blowing Or Suction written by H. S. Mickley and published by . This book was released on 1954 with total page 166 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effect on the boundary layer of sucking or blowing air through a porous flat plate into or out of a main air stream flowing parallel to the plate was studied theoretically and experimentally.
