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Heat Transfer To 0 Degree And 75 Degrees Swept Blunt Leading Edges In Free Flight At Mach Numbers From 190 To 307
Download Heat Transfer To 0 Degree And 75 Degrees Swept Blunt Leading Edges In Free Flight At Mach Numbers From 190 To 307 full books in PDF, epub, and Kindle. Read online Heat Transfer To 0 Degree And 75 Degrees Swept Blunt Leading Edges In Free Flight At Mach Numbers From 190 To 307 ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 by : Robert L. O'Neal
Download or read book Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 written by Robert L. O'Neal and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer to 0 Degree and 75 Degrees Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 by : ROBERT L. O'NEAL
Download or read book Heat Transfer to 0 Degree and 75 Degrees Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 written by ROBERT L. O'NEAL and published by . This book was released on 1962 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: A flight investigation of a rocket-powered model was conducted to study the heat transfer to wing leading edges in the vicinity of their juncture with a cylindrical body. Heat-transfer data were obtained on leading edges of 3/4-inch diameter at sweep angles of 0 and 75 degrees, Mach numbers from 1.90 to 3.07, and Reynolds numbers based on leading-edge diameter from 8.05 to 11.80 times 10 to the 5th power. The measured heating rates of both the 0 and 75 degrees swept leading edges were of the magnitude predicted by turbulent theory rather than by laminar theory. It is believed that the high level of heating observed on the leading edges was due to the influence of conditions existing in the turbulent boundary layer of the body. Comparison of the average measured heating on the cylindrical portions of both the swept and unswept leading edges indicates that the heating of the unswept segment was generally about twice that of the swept segment. (Author).
Book Synopsis Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 by : Robert L. O'Neal
Download or read book Heat Transfer to 0 Degree and 75 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 written by Robert L. O'Neal and published by . This book was released on 1962 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer to 0° and 75° Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 by : Robert L. O'Neal
Download or read book Heat Transfer to 0° and 75° Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.90 to 3.07 written by Robert L. O'Neal and published by . This book was released on 1962 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer to 36.75 and 45 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.70 to 2.99 and From 2.50 to 4.05 by :
Download or read book Heat Transfer to 36.75 and 45 Degree Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.70 to 2.99 and From 2.50 to 4.05 written by and published by . This book was released on 1960 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer to 36.75° and 45° Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.70 to 2.99 and from 2.50 to 4.05 by : Robert L. O'Neal
Download or read book Heat Transfer to 36.75° and 45° Swept Blunt Leading Edges in Free Flight at Mach Numbers from 1.70 to 2.99 and from 2.50 to 4.05 written by Robert L. O'Neal and published by . This book was released on 1960 with total page 37 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Free-flight Measurements of Pressure and Heat Transfer on a Blunt Leading-edge Caret Wing at Design and Off-design Mach Numbers (M Infinity by : G.H. Greenwood
Download or read book Free-flight Measurements of Pressure and Heat Transfer on a Blunt Leading-edge Caret Wing at Design and Off-design Mach Numbers (M Infinity written by G.H. Greenwood and published by . This book was released on 1970 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Free-flight Measurements of Pressure and Heat Transfer on a Blunt Leading-edge Caret Wing at Design and Off-design MACH Numbers (M Equal 0.9 to 3.36 by : Aeronautical Research Council
Download or read book Free-flight Measurements of Pressure and Heat Transfer on a Blunt Leading-edge Caret Wing at Design and Off-design MACH Numbers (M Equal 0.9 to 3.36 written by Aeronautical Research Council and published by . This book was released on 1971 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer and Pressure Distributions at a Mach Number of 6 for 70 Deg Swept Slab Wings with Sharp and Spherical Noses and Cylindrical Leading Edges by :
Download or read book Heat Transfer and Pressure Distributions at a Mach Number of 6 for 70 Deg Swept Slab Wings with Sharp and Spherical Noses and Cylindrical Leading Edges written by and published by . This book was released on 1962 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Characteristics of Blunt Two-and Three-dimensional Bodies at Supersonic Speeds by : Glen Goodwin
Download or read book Heat-transfer Characteristics of Blunt Two-and Three-dimensional Bodies at Supersonic Speeds written by Glen Goodwin and published by . This book was released on 1956 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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 Investigation of Heat Transfer on a Finned Body in the Region of Fin-body Interference in Free Flight at Mach Numbers Up to 11 by :
Download or read book Investigation of Heat Transfer on a Finned Body in the Region of Fin-body Interference in Free Flight at Mach Numbers Up to 11 written by and published by . This book was released on 1962 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer Measured in Free Flight on a Slightly Blunted 25 Degree Cone-cylinder-flare Configuration at Mach Numbers Up to 9.89 by : Dorothy B. Lee
Download or read book Heat Transfer Measured in Free Flight on a Slightly Blunted 25 Degree Cone-cylinder-flare Configuration at Mach Numbers Up to 9.89 written by Dorothy B. Lee and published by . This book was released on 1958 with total page 63 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Surface Pressure Tests on Blunt Slab Wings Swept to 0, 45, 60, and 70 Degrees at Mach Numbers 1.71, 2.5, 4.0, 7.6 and Angles of Attack Up to 40 Degrees by : FRANK H. DURGIN
Download or read book Surface Pressure Tests on Blunt Slab Wings Swept to 0, 45, 60, and 70 Degrees at Mach Numbers 1.71, 2.5, 4.0, 7.6 and Angles of Attack Up to 40 Degrees written by FRANK H. DURGIN and published by . This book was released on 1960 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation of the two-dimensional surface pressures on blunt, swept, slab wings was conducted. The test was undertaken as part of a more general program in which the flow field behind a blunt slab wing at high angles ofATTACK IN SUPERSONIC AND HYPERSONIC FLOW IS BEING STUDIED. The purpose of the present test was to determine experimentally the effects of leading edge blunting and sweep and angle of attack on the surface pressure distribution of a flat plate. Four models having 0, 45, 60, and 70 degrees of leading edge sweep were built, instrumented with 16 to 18 pressure taps and tested at Mach numbers 1.71, 2.5, 4.0, and 7.6 through an angle of attack range of -24 to 40 degrees. Each wing has a 3/8 inch cylindrical leading edge and flat upper, lower, and base surfaces. Tabulated and graphical presentation of the pressure data is included. (Author).
Book Synopsis Hypersonic and High Temperature Gas Dynamics by : John David Anderson
Download or read book Hypersonic and High Temperature Gas Dynamics written by John David Anderson and published by AIAA. This book was released on 1989 with total page 710 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book is a self-contained text for those students and readers interested in learning hypersonic flow and high-temperature gas dynamics. It assumes no prior familiarity with either subject on the part of the reader. If you have never studied hypersonic and/or high-temperature gas dynamics before, and if you have never worked extensively in the area, then this book is for you. On the other hand, if you have worked and/or are working in these areas, and you want a cohesive presentation of the fundamentals, a development of important theory and techniques, a discussion of the salient results with emphasis on the physical aspects, and a presentation of modern thinking in these areas, then this book is also for you. In other words, this book is designed for two roles: 1) as an effective classroom text that can be used with ease by the instructor, and understood with ease by the student; and 2) as a viable, professional working tool for engineers, scientists, and managers who have any contact in their jobs with hypersonic and/or high-temperature flow.
Book Synopsis Introduction to Aircraft Flight Mechanics by : Thomas R. Yechout
Download or read book Introduction to Aircraft Flight Mechanics written by Thomas R. Yechout and published by AIAA. This book was released on 2003 with total page 666 pages. Available in PDF, EPUB and Kindle. Book excerpt: Based on a 15-year successful approach to teaching aircraft flight mechanics at the US Air Force Academy, this text explains the concepts and derivations of equations for aircraft flight mechanics. It covers aircraft performance, static stability, aircraft dynamics stability and feedback control.
