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Additional Heat Transfer Measurements Obtained In Free Flight On A Hemispherical Concave Nose At Mach Numbers Up To 71
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Book Synopsis Additional Heat Transfer Measurements Obtained in Free Flight on a Hemispherical Concave Nose at Mach Numbers Up to 7.1 by : Jack Levine
Download or read book Additional Heat Transfer Measurements Obtained in Free Flight on a Hemispherical Concave Nose at Mach Numbers Up to 7.1 written by Jack Levine and published by . This book was released on 1961 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer Measurements on a 5.5-inch-diameter Hemispherical Concave Nose in Free Flight at Mach Numbers Up to 6.6 by : Jack Levine
Download or read book Heat-transfer Measurements on a 5.5-inch-diameter Hemispherical Concave Nose in Free Flight at Mach Numbers Up to 6.6 written by Jack Levine and published by . This book was released on 1958 with total page 47 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Book Synopsis 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 by : Howard S. Carter
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.
Book Synopsis 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 by : James R. Hall
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:
Book Synopsis Heat-transfer Measurements on a Blunt Spherical-segment Nose to a Mach Number of 15.1 and Flight Performance of the Rocket-propelled Model to a Mach Number of 17.8 by : Charles B. Rumsey
Download or read book Heat-transfer Measurements on a Blunt Spherical-segment Nose to a Mach Number of 15.1 and Flight Performance of the Rocket-propelled Model to a Mach Number of 17.8 written by Charles B. Rumsey and published by . This book was released on 1959 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis 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 by : Charles B. Rumsey
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.
Book Synopsis Heat-transfer and Pressure Measurements on a Concove-nose Cylinder for a Mach Number Range of 2.49 to 4.44 by : Stallings, Jr. (Robert L.)
Download or read book Heat-transfer and Pressure Measurements on a Concove-nose Cylinder for a Mach Number Range of 2.49 to 4.44 written by Stallings, Jr. (Robert L.) and published by . This book was released on 1959 with total page 21 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:
Book Synopsis Aerodynamic-heating Data Obtained from Free-flight Tests Between Mach Numbers of 1 and 5 by : Charles Bertrand Rumsey
Download or read book Aerodynamic-heating Data Obtained from Free-flight Tests Between Mach Numbers of 1 and 5 written by Charles Bertrand Rumsey and published by . This book was released on 1960 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer and Pressure Measurement on a 5-inch Hemispherical Concave Nose at a Mach Number of 2.0 by : Langley Aeronautical Laboratory
Download or read book Heat Transfer and Pressure Measurement on a 5-inch Hemispherical Concave Nose at a Mach Number of 2.0 written by Langley Aeronautical Laboratory and published by Hassell Street Press. This book was released on 2021-09-10 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: This work has been selected by scholars as being culturally important and is part of the knowledge base of civilization as we know it. This work is in the public domain in the United States of America, and possibly other nations. Within the United States, you may freely copy and distribute this work, as no entity (individual or corporate) has a copyright on the body of the work. Scholars believe, and we concur, that this work is important enough to be preserved, reproduced, and made generally available to the public. To ensure a quality reading experience, this work has been proofread and republished using a format that seamlessly blends the original graphical elements with text in an easy-to-read typeface. We appreciate your support of the preservation process, and thank you for being an important part of keeping this knowledge alive and relevant.
Book Synopsis Heat-transfer Measurements in Free Flight at Mach Numbers Up to 14.6 on a Flat-faced Conical Nose with a Total Angle of 29 Degrees by : Charles B. Rumsey
Download or read book Heat-transfer Measurements in Free Flight at Mach Numbers Up to 14.6 on a Flat-faced Conical Nose with a Total Angle of 29 Degrees written by Charles B. Rumsey and published by . This book was released on 1958 with total page 43 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Heating and Boundary-layer Transition on a 1/10-power Nose Shape in Free Flight at Mach Numbers Up to 6.7 and Free-stream Reynolds Numbers Up to 16 X 10(6) by : Benjamine J. Garland
Download or read book Aerodynamic Heating and Boundary-layer Transition on a 1/10-power Nose Shape in Free Flight at Mach Numbers Up to 6.7 and Free-stream Reynolds Numbers Up to 16 X 10(6) written by Benjamine J. Garland and published by . This book was released on 1962 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of Aerodynamic Heat Transfer and Boundary-layer Transition on a 10 Degree 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 Degree 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 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer Measurements on a Blunt Spherical-segment Nose to a Mach Number of 15.1 and Flight Performance of the Rocket- Propelled Model to a Mach Number of 17.8 by :
Download or read book Heat-transfer Measurements on a Blunt Spherical-segment Nose to a Mach Number of 15.1 and Flight Performance of the Rocket- Propelled Model to a Mach Number of 17.8 written by and published by . This book was released on 1959 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
