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Investigation Of The Laminar Aerodynamic Heat Transfer Characteristics Of A Hemisphere Cylinder In The Langley 11 Inch Hypersonic Tunnel At A Mach Number Of 68
Download Investigation Of The Laminar Aerodynamic Heat Transfer Characteristics Of A Hemisphere Cylinder In The Langley 11 Inch Hypersonic Tunnel At A Mach Number Of 68 full books in PDF, epub, and Kindle. Read online Investigation Of The Laminar Aerodynamic Heat Transfer Characteristics Of A Hemisphere Cylinder In The Langley 11 Inch Hypersonic Tunnel At A Mach Number Of 68 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8 by : Davis H. Crawford
Download or read book Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8 written by Davis H. Crawford and published by . This book was released on 1956 with total page 680 pages. Available in PDF, EPUB and Kindle. Book excerpt: At the stagnation point, the theory of Sibulkin, using the diameter and conditions behind the normal shock, was in good agreement with the experiment when the velocity graident at the stagnation opint appropriate to the free-stream Mach number was used.
Book Synopsis Index of NACA Technical Publications by : United States. National Advisory Committee for Aeronautics
Download or read book Index of NACA Technical Publications written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1959 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Selected Listing of NASA Scientific and Technical Reports for ... by :
Download or read book A Selected Listing of NASA Scientific and Technical Reports for ... written by and published by . This book was released on 1957 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Annual Report of the National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics
Download or read book Annual Report of the National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1958 with total page 1516 pages. Available in PDF, EPUB and Kindle. Book excerpt: Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Book Synopsis Cumulative Title Index to United States Public Documents, 1789-1976 by : Daniel W. Lester
Download or read book Cumulative Title Index to United States Public Documents, 1789-1976 written by Daniel W. Lester and published by . This book was released on 1980 with total page 686 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Subject Catalog by : Library of Congress
Download or read book Subject Catalog written by Library of Congress and published by . This book was released on 1955 with total page 660 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Library of Congress Catalog by : Library of Congress
Download or read book Library of Congress Catalog written by Library of Congress and published by . This book was released on 1955 with total page 658 pages. Available in PDF, EPUB and Kindle. Book excerpt: A cumulative list of works represented by Library of Congress printed cards.
Book Synopsis Store Separation by : Leon H. Schindel
Download or read book Store Separation written by Leon H. Schindel and published by . This book was released on 1975 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt: This AGARDograph is a systematic collection of experimental results for use of engineers and designers, limited to externally carried, unpowered, unguided stores. In the sections dealing with store trajectories, the physical situation is described, the method of solution is indicated, and the final results are presented. Emphasis is on store motion in traversing the parent aircraft flowfield, with criteria for safe separation and methods of calculating flight path. Windtunnel test techniques are described, and some information on flight testing given. Analytical treatment is compared with flight and tunnel results. There are brief mentions of ejection systems and the effect of stores on aircraft performance.
Book Synopsis Library of Congress Catalogs by : Library of Congress
Download or read book Library of Congress Catalogs written by Library of Congress and published by . This book was released on 1960 with total page 658 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Investigation of the Flow Over a Spiked-nose Hemisphere-cylinder at a Mach Number of 6.8 by : Davis H. Crawford
Download or read book Investigation of the Flow Over a Spiked-nose Hemisphere-cylinder at a Mach Number of 6.8 written by Davis H. Crawford and published by . This book was released on 1959 with total page 68 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book The NATA Code written by W. L. Bade and published by . This book was released on 1975 with total page 236 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computer program for calculating quasi-one-dimensional gas flow in axisymmetric and two-dimensional nozzles and rectangular channels is presented. Flow is assumed to start from a state of thermochemical equilibrium at a high temperature in an upstream reservoir. The program provides solutions based on frozen chemistry, chemical equilibrium, and nonequilibrium flow with finite reaction rates. Electronic nonequilibrium effects can be included using a two-temperature model. An approximate laminar boundary layer calculation is given for the shear and heat flux on the nozzle wall. Boundary layer displacement effects on the inviscid flow are considered also. Chemical equilibrium and transport property calculations are provided by subroutines. The code contains precoded thermochemical, chemical kinetic, and transport cross section data for high-temperature air, CO2-N2-Ar mixtures, helium, and argon. It provides calculations of the stagnation conditions on axisymmetric or two-dimensional models, and of the conditions on the flat surface of a blunt wedge. The primary purpose of the code is to describe the flow conditions and test conditions in electric arc heated wind tunnels.
Book Synopsis NASA Contractor Report by : United States. National Aeronautics and Space Administration
Download or read book NASA Contractor Report written by United States. National Aeronautics and Space Administration and published by . This book was released on 1975 with total page 798 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721040322 Total Pages :100 pages Book Rating :4.0/5 (43 download)
Book Synopsis X-33 (Rev-F) Aeroheating Results of Test 6770 in NASA Langley 20-Inch Mach 6 Air Tunnel by : National Aeronautics and Space Administration (NASA)
Download or read book X-33 (Rev-F) Aeroheating Results of Test 6770 in NASA Langley 20-Inch Mach 6 Air Tunnel written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-12 with total page 100 pages. Available in PDF, EPUB and Kindle. Book excerpt: Aeroheating characteristics of the X-33 Rev-F configuration have been experimentally examined in the Langley 20-Inch Mach 6 Air Tunnel (Test 6770). Global surface heat transfer distributions, surface streamline patterns, and shock shapes were measured on a 0.013-scale model at Mach 6 in air. Parametric variations include angles-of-attack of 20-deg, 30-deg, and 40-deg; Reynolds numbers based on model length of 0.9 to 4.9 million; and body-flap deflections of 10-deg and 20-deg. The effects of discrete roughness elements on boundary layer transition, which included trip height, size, and location, both on and off the windward centerline, were investigated. This document is intended to serve as a quick release of preliminary data to the X-33 program; analysis is limited to observations of the experimental trends in order to expedite dissemination.Berry, Scott A. and Horvath, Thomas J. and Kowalkowski, Matthew K. and Liechty, Derek S.Langley Research CenterX-33 REUSABLE LAUNCH VEHICLE; AERODYNAMIC HEATING; AERODYNAMIC CONFIGURATIONS; WIND TUNNEL TESTS; HYPERSONIC SPEED; HEAT TRANSFER; BOUNDARY LAYER TRANSITION; AEROTHERMODYNAMICS; WIND TUNNEL MODELS; REYNOLDS NUMBER; FLAPPING; THERMOGRAPHY; SCALE MODELS; SPACECRAFT MODELS
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 Effect of Roughness on Heat Transfer to Hemisphere Cylinders at Mach Numbers 10.4 and 11.4 by : James C. Dunavant
Download or read book Effect of Roughness on Heat Transfer to Hemisphere Cylinders at Mach Numbers 10.4 and 11.4 written by James C. Dunavant and published by . This book was released on 1967 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Local Heat Transfer and Recovery Temperatures on a Yawed Cylinder at a Mach Number of 4.15 and High Reynolds Numbers by : Ivan E. Beckwith
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.
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.
