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Download Heat Transfer And Pressure Measurements On A Concove Nose Cylinder For A Mach Number Range Of 249 To 444 full books in PDF, epub, and Kindle. Read online Heat Transfer And Pressure Measurements On A Concove Nose Cylinder For A Mach Number Range Of 249 To 444 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Author :
Publisher :
ISBN 13 :
Total Pages : 26 pages
Book Rating : 4.:/5 (317 download)
Download or read book Heat-transfer and Pressure Measurements on a Concave-nose Cylinder for Mach Number Range of 2.49 to 4.44 written by and published by . This book was released on 1959 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : J. Thomas Markley
Publisher :
ISBN 13 :
Total Pages : 24 pages
Book Rating : 4.3/5 (91 download)
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 J. Thomas Markley and published by . This book was released on 1958 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The concave-nose stagnation-point heating is 40 percent of that of a hemisphere nose shape having the same diameter. At angles of attack of ℗±5© and ℗± 10© there is no increase in heating of the nose. Total pressures behind the shock were experienced up to 60© on the concave part for all angles of attack. The tests were made under sea-level conditions for a Reynolds number per foot of about 14 x 106.
Author : Richard D. Wagner
Publisher :
ISBN 13 :
Total Pages : 44 pages
Book Rating : 4.:/5 (31 download)
Download or read book Laminar Heat-transfer and Pressure-distribution Studies on a Series of Reentry Nose Shapes at a Mach Number of 19.4 in Helium written by Richard D. Wagner and published by . This book was released on 1961 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : William E. Stoney
Publisher :
ISBN 13 :
Total Pages : 16 pages
Book Rating : 4.3/5 (91 download)
Download or read book Local Heat Transfer to Blunt Noses at High Supersonic Speeds written by William E. Stoney and published by . This book was released on 1957 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Morton Cooper
Publisher :
ISBN 13 :
Total Pages : 19 pages
Book Rating : 4.:/5 (11 download)
Download or read book Heat-transfer Measurements on a Concave Hemispherical Nose with Unsteady-flow Effects at Mach Numbers of 1.98 and 4.95 written by Morton Cooper and published by . This book was released on 1958 with total page 19 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Philip E. Everhart
Publisher :
ISBN 13 :
Total Pages : 66 pages
Book Rating : 4.:/5 (31 download)
Download or read book Measurements of the Surface Flows, Heat Transfer, Pressure Distribution, and Longitudinal Stability of a Mercury Capsule Model at Mach Numbers of 6.9 and 9.6 written by Philip E. Everhart and published by . This book was released on 1961 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : William E. Stoney
Publisher :
ISBN 13 :
Total Pages : 38 pages
Book Rating : 4.:/5 (25 download)
Download or read book Heat-transfer and Pressure Measurements on Flat-faced Cylinders at a Mach Number of 2 written by William E. Stoney and published by . This book was released on 1958 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Flat-faced cylinders of 12-inch dtameter and 4-inch diameter were tested at a Mach number of 2 and sea-level conditions in the preflight jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va. Both pressure distributions and heat-transfer rates were measured.
Author : Thorval Tendeland
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.:/5 (317 download)
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.
Author : Paul F. Brinich
Publisher :
ISBN 13 :
Total Pages : 56 pages
Book Rating : 4.:/5 (31 download)
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:
Author : Benjamine J. Garland
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.:/5 (31 download)
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:
Author : Kenneth Sutton
Publisher :
ISBN 13 :
Total Pages : 76 pages
Book Rating : 4.:/5 (31 download)
Download or read book Descriptions and Operating Parameters of a Mach 2 Nozzle System for the Langley 11-inch Ceramic-heated Tunnel written by Kenneth Sutton and published by . This book was released on 1968 with total page 76 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Langley Aeronautical Laboratory
Publisher : Hassell Street Press
ISBN 13 : 9781015043015
Total Pages : 30 pages
Book Rating : 4.0/5 (43 download)
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 Langley Aeronautical Laboratory and published by Hassell Street Press. This book was released on 2021-09-10 with total page 30 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.
Author : RICHARD D. JR. WAGNER
Publisher :
ISBN 13 :
Total Pages : 1 pages
Book Rating : 4.:/5 (227 download)
Download or read book Laminar Heat-transfer and Pressure-distribution Studies on a Series of Reentry Nose Shapes at a Mach Number of 19.4 in Helium written by RICHARD D. JR. WAGNER and published by . This book was released on 1961 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted in the 2-in. helium tunnel at the Langley Research Center at a Mach number of 19.4 to determine the pressure distributions and heat-transfer characteristics of a family of reentry nose shapes. The pressure and heat-transfer-rate distributions on the nose shapes are compared with theoretical predictions to ascertain the limitations and validity of the theories at hypersonic speeds. The experimental results were found to be adequately predicted by existing theories. Two of the nose shapes were tested with variable-length flow-separation spikes. The results obtained by previous investigators of spike-nose bodies were found to prevail at the higher Mach number of the present investigation. (Author).
Author : Robert A. Jones
Publisher :
ISBN 13 :
Total Pages : 40 pages
Book Rating : 4.:/5 (11 download)
Download or read book Heat Transfer and Pressure Distributions at a Mach Number of 6 for 70 Swept Slab Wings with Sharp and Spherical Noses and Cylindrical Leading Edges written by Robert A. Jones and published by . This book was released on 1962 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Roland D. English
Publisher :
ISBN 13 :
Total Pages : 30 pages
Book Rating : 4.:/5 (31 download)
Download or read book Variation in Heat Transfer During Transient Heation of a Hemisphere at a Mach Numer of 2 written by Roland D. English and published by . This book was released on 1960 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : William M. Bland
Publisher :
ISBN 13 :
Total Pages : 36 pages
Book Rating : 4.3/5 (126 download)
Download or read book Some Effects of Heat Transfer at Mach Number 2.0 at Stagnation Temperatures Between 2,310° and 3,500° R on a Magnesium Fin with Several Leading-edge Modifications written by William M. Bland and published by . This book was released on 1957 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Four models of a thin magnesium fin, with the leading edge swept back 35°, have been tested in the preflight high-temperature jet of the Langley Pilotless Aircraft Research Station at Wallops Island, Va., at a Mach number of 2.0 for various stagnation temperatures between 2,310° and 3,500° R. This exploratory investigation was made to determine some effects of aerodynamic heating at high stagnation temperatures on the leading edges of fins and to determine the relative effectiveness of several leading-edge protective schemes.
Author : Paige B. Burbank
Publisher :
ISBN 13 :
Total Pages : 52 pages
Book Rating : 4.3/5 (91 download)
Download or read book The Aerodynamic Design and Calibration of an Asymmetric Variable Mach Number Nozzle with Sliding Block for the Mach Number Range 1.27 to 2.75 written by Paige B. Burbank and published by . This book was released on 1951 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method of designing an aymmetric, fixed-geometry, variable Mach number nozzle has been developed by using the method of characteristics. A small nozzle conforming to the analytically determined ordinates was a constructed and calibrated over a range of Mach numbers extending from 1.27 to 2.75. The results show the variation in Mach number to be plus or minus 0.02 or less and in the flow direction to be plus or minus 0.2 degrees within the test section. The range of Mach numbers 1.27 to 2.75 was obtained by translating the lower block in a straight line parallel to the test-section center line for a distance of 2.17 test-section heights.
