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 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Local Heat Transfer and Recovery Temperatures on Yawed Cylinder at Mach Number of 4 15 and High Reynolds Numbers with List of References written by and published by . This book was released on 1959 with total page 6 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 25 pages. Available in PDF, EPUB and Kindle. Book excerpt: Local heat transfer, equilibrium temperatures, and pressure have been measured on a circular cylinder for yaw angles from 0° to 60° and Reynolds numbers from 1X106 to 4X106. Increasing the yaw angle from 0° to 40° generally caused large increases in local heat-transfer coefficients followed by a decrease as the yaw angle was increased to 60°. The level of heating rates and the type if chordwise distribution indicated that a flow mechanism different from the conventional transitional boundary layer may exist for the intermediate yaw angles.
Download or read book Local Heat Transfer and Recovery Temperatures on Yawed Cylinder at Mach Numbers of 4 15 and High Reynolds Numbers with List of References written by and published by . This book was released on 1962 with total page 25 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 Free flight Measurements of Aerodynamic Heat Transfer to Mach Number 3 9 and of Drag to Mach Number 6 9 of a Fin stabilized Cone cylinder Configuration written by Charles B. Rumsey and published by . This book was released on 1955 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aerodynamic-heat-transfer measurements have been made at a station on the 10 degree total angle conical nose of a rocket-propelled model at flight Mach numbers of 1.4 to 3.9. The corresponding values of local Reynolds number varied from 18,000,000 to 46,000,000 and the ratio of skin temperature to local static temperature varied from 1.2 to 2.4. The experimental data, reduced to Stanton number, were in fair agreement with values predicted by Van Driest's theory for heat transfer on a cone with turbulent flow from the nose tip.
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 On the Temperature Distribution Behind Cylinders in a Flow written by Ackeret Jakob and published by . This book was released on 1959 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Heat Transfer and Pressure Measurements on a Flat Face Cylinder at a Mach Number Range of 2 49 to 4 44 written by Paige B. Burbank and published by . This book was released on 1959 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Free flight Investigation of Heat Transfer to an Unswept Cylinder Subjected to an Incident Shock and Flow Interference from an Upstream Body at Mach Numbers Up to 5 50 written by Howard S. Carter and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Heat-transfer rates have been measured in free flight along the stagnation line of an unswept cylinder mounted transversely on an axial cylinder so that the shock wave from the hemispherical nose of the axial cylinder intersected the bow shock of the unswept transverse cylinder. Data were obtained at Mach numbers from 2.53 to 5.50 and at Reynolds numbers based on the transverse cylinder diameter from 1.00 x 106 to 1.87 x 106. Shadowgraph pictures made in a wind tunnel showed that the flow field was influenced by boundary-layer separation on the axial cylinder and by end effects on the transverse cylinder as well as by the intersecting shocks. Under these conditions, the measured heat-transfer rates had inconsistent variations both in magnitude and distribution which precluded separating the effects of these disturbances. The general magnitude of the measured heating rates at Mach numbers up to 3 was from 0.1 to 0.5 of the theoretical laminar heating rates along the stagnation line for an infinite unswept cylinder in undisturbed flow. At Mach numbers above 4 the measured heating rates were from 1.5 to 2 times the theoretical rates.
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 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 Heat Transfer and Pressure Drop for a Gas at High Temperature written by Monty E. Davenport and published by . This book was released on 1961 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Experimental Study of Heat Transfer to Small Cylinders in a Subsonic High temperature Gas Stream written by George E. Glawe and published by . This book was released on 1957 with total page 820 pages. Available in PDF, EPUB and Kindle. Book excerpt: A Nusselt-Reynolds number relation for cylindrical thermocouple wires in crossflow was obtained from the experimental determination of time constants. Tests were conducted in exhaust gas over a temperature range of 2000 to 3400 R, a Mach number range of 0.3 to 0.8, and a static-pressure range from 2/3 to 1-1/3 atmospheres, yielding a Reynolds number range of 450 to 3000. The correlation obtained is Nu=(0.428 plus or minus 0.003) times the square root of Re with average deviations of a single observation of 8.5 percent. This relation is the same as one previously reported for room-temperature conditions.
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 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 Heat Transfer and Recovery Temperatures on a Sphere with Laminar Transitional and Turbulent Boundary Layers at Mach Numbers of 2 00 and 4 15 written by Ivan E. Beckwith and published by . This book was released on 1957 with total page 59 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was made of the pressure and equilibrium-temperature distributions on sphere at Mach numbers of 2.00 and 4.15. The local aerodynamic best transfer was also measured on a sphere at a Mach number of 2.00 and on a hemisphere-cylinder at a Mach number of 4.15. The Reynolds number range for these tests was from 1.5 x 10 to the 6th power to 8.1 x 10 to the 6th power, based on free-stream conditions and the diameter of the spheres.
