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Pressure And Heat Transfer Measurements On The Flat Face Of A Blunted 10 Half Cone Body Semidisk At A Mach Number Of 615
Download Pressure And Heat Transfer Measurements On The Flat Face Of A Blunted 10 Half Cone Body Semidisk At A Mach Number Of 615 full books in PDF, epub, and Kindle. Read online Pressure And Heat Transfer Measurements On The Flat Face Of A Blunted 10 Half Cone Body Semidisk At A Mach Number Of 615 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Pressure and Heat-transfer Measurements on the Flat Face of a Blunted 10 ̊half-cone Body (semidisk) at a Mach Number of 6.15 by : P. Calvin Stainback
Download or read book Pressure and Heat-transfer Measurements on the Flat Face of a Blunted 10 ̊half-cone Body (semidisk) at a Mach Number of 6.15 written by P. Calvin Stainback and published by . This book was released on 1963 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Applied Mechanics Reviews written by and published by . This book was released on 1963 with total page 1196 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Laminar Heat-transfer and Pressure Measurements at a Mach Number of 6 on a Sharp and Blunt 15° Half-angle Cones at Angles of Attack Up to 90° by : Raul Jorge Conti
Download or read book Laminar Heat-transfer and Pressure Measurements at a Mach Number of 6 on a Sharp and Blunt 15° Half-angle Cones at Angles of Attack Up to 90° written by Raul Jorge Conti and published by . This book was released on 1961 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt: Two circulation conical configurations having 15° half-angles were tested in laminar boundary layer at a Mach number of 6 and angles of attack up to 90°. One cone had a sharp nose and a fineness ratio of 1.87 and the other had a spherically blunted nose with a bluntness ratio of 0.1428 and a fineness ratio of 1.66. Pressure measurements and schlieren pictures of the flow showed that near-conical flow existed above 70° high pressure areas were present near the base and the bow shock wave was considerably curved.
Book Synopsis Heat-Transfer and Pressure Measurements on a Flat-Face Cylinder at a Mach Number Range of 2.49 to 4.44 by : Paige B. Burbank
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:
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 Convective Heat Transfer to a Lifting Flat-faced-cone Entry Body by : James E. Terry
Download or read book Convective Heat Transfer to a Lifting Flat-faced-cone Entry Body written by James E. Terry and published by . This book was released on 1961 with total page 46 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat-transfer and Pressure Distributions on Spherically Blunted 25 ̊half-angle Cone at Mach 8 and Angles of Attack Up to 90 ̊ by : Dennis M. Bushnell
Download or read book Heat-transfer and Pressure Distributions on Spherically Blunted 25 ̊half-angle Cone at Mach 8 and Angles of Attack Up to 90 ̊ written by Dennis M. Bushnell and published by . This book was released on 1968 with total page 40 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 Aerodynamic Heating on the Corrugated Surface of a 10.20 Half-angle Blunted Cone at Mach 6.7 by : Irving Weinstein
Download or read book Aerodynamic Heating on the Corrugated Surface of a 10.20 Half-angle Blunted Cone at Mach 6.7 written by Irving Weinstein and published by . This book was released on 1981 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer to a Hemispherically Blunted 9 Deg Half-angle Cone During Free Flight at Mach Numbers Up to 20.8 by :
Download or read book Heat Transfer to a Hemispherically Blunted 9 Deg Half-angle Cone During Free Flight at Mach Numbers Up to 20.8 written by and published by . This book was released on 1963 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Real-gas Effects in Critical-flow-through Nozzles and Tabulated Thermodynamic Properties by : Robert Clinton Johnson
Download or read book Real-gas Effects in Critical-flow-through Nozzles and Tabulated Thermodynamic Properties written by Robert Clinton Johnson and published by . This book was released on 1965 with total page 142 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Theoretical Analysis of Effects of Ablation on Heat Transfer to an Arbitrary Axisymmetric Body by : Robert T. Swann
Download or read book Theoretical Analysis of Effects of Ablation on Heat Transfer to an Arbitrary Axisymmetric Body written by Robert T. Swann and published by . This book was released on 1961 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Collection and Analysis of Wind-tunnel Data on the Characteristics of Isolated Tail Surfaces with and Without End Plates by : WIlliam R. Bates
Download or read book Collection and Analysis of Wind-tunnel Data on the Characteristics of Isolated Tail Surfaces with and Without End Plates written by WIlliam R. Bates and published by . This book was released on 1947 with total page 538 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic characteristics of 19 isolated tail surfaces have been determined by wind-tunnel tests and tests have also been made of rectangular airfoils of various aspect ratios with and without double end plates of various shapes. Thes data from these tests have been collected and analyzed.
Book Synopsis Design and Operational Performance of a 150-kilowatt Sodium Flash-vaporization Facility by : Landon R. Nichols
Download or read book Design and Operational Performance of a 150-kilowatt Sodium Flash-vaporization Facility written by Landon R. Nichols and published by . This book was released on 1963 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Langley Full-scale-tunnel Investigation of the Fuselage Boundary Layer on a Typical Fighter Airplane with a Single Liquid-cooled Engine by : K. R. Czarnecki
Download or read book Langley Full-scale-tunnel Investigation of the Fuselage Boundary Layer on a Typical Fighter Airplane with a Single Liquid-cooled Engine written by K. R. Czarnecki and published by . This book was released on 1946 with total page 20 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation has been made in the Langley full-scale tunnel to determine the thickness and shape of profile of the boundary layer on the fuselage of a typical monoplane fighter airplane with a single liquid-cooled engine. The results showed that, for the range of angles of attack and fuselage stations investigated, the maximum displacement thickness was nearly 1.2 inches and was at the most rearward station (81.6 percent of the fuselage length). The displacement thickness was found to be greatly affected by the pressure gradients over the windshield-canopy combination and in the wing-fuselage juncture. An average value for the shape parameter between 1.3 and 1.4 was obtained for the turbulent boundary layer.
Book Synopsis Notes on the Stalling of Vertical Tail Surfaces and on Fin Design by : F. L. Thompson
Download or read book Notes on the Stalling of Vertical Tail Surfaces and on Fin Design written by F. L. Thompson and published by . This book was released on 1940 with total page 566 pages. Available in PDF, EPUB and Kindle. Book excerpt: It may be concluded that the stalling of vertical tail surfaces is not in itself a dangerous condition. Provided sufficient directional stability exists at large angles of sideslip, the tail stall may occur with modern airplanes, as with those of the past, without the knowledge of or concern to the pilot.
