Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Pressure And Heat Transfer Measurements On The Flat Face Of A Blunted 10 Degree Half Cone Body Semidisk At A Mach Number Of 615
Download Pressure And Heat Transfer Measurements On The Flat Face Of A Blunted 10 Degree 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 Degree 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 A Flight Determination of the Tolerable Range of Effective Dihedral on a Conventional Fighter Airplane by : Charles J. Liddell
Download or read book A Flight Determination of the Tolerable Range of Effective Dihedral on a Conventional Fighter Airplane written by Charles J. Liddell and published by . This book was released on 1949 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt: A conventional fighter airplane was equipped with a special device for varying the effective dihedral in flight. A survey of pilot's opinions was made to determine which values of effective dihedral were intolerable. The relation between the findings and the present Air Force-Navy stability and control specifications is discussed.
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 Earth Reflected Solar Radiation Incident Upon an Arbitrarily Oriented Spinning Flat Plate by : Fred G. Cunningham
Download or read book Earth Reflected Solar Radiation Incident Upon an Arbitrarily Oriented Spinning Flat Plate written by Fred G. Cunningham and published by . This book was released on 1963 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt:
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.
Book Synopsis NASA Technical Translation by : United States. National Aeronautics and Space Administration
Download or read book NASA Technical Translation written by United States. National Aeronautics and Space Administration and published by . This book was released on 1970 with total page 230 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wartime Report ... A-. by : United States. National Advisory Committee for Aeronautics
Download or read book Wartime Report ... A-. written by United States. National Advisory Committee for Aeronautics and published by . This book was released on with total page 544 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1977 with total page 492 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Technical Aerodynamics by : K. D. Wood
Download or read book Technical Aerodynamics written by K. D. Wood and published by Lulu.com. This book was released on 2019-11-15 with total page 530 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is the third edition of a text much loved by engineers and aeronautical engineering students because it relates fundamental aerodynamic concepts to the practical facts of engineering design and teaches the two together. It is the companion to the 10th Edition (1954) of the same author's Airplane Design.In this improved facsimile edition, most of the front matter has been transcribed, the errata have been corrected, new headers and footers have been added and the pagination has been corrected so that odd pages are all on the right side. Some improvements have also been made to photos and line art.All other pages are page images of the original, printed Third Edition.
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 Technical Aerodynamics by : Karl Dawson Wood
Download or read book Technical Aerodynamics written by Karl Dawson Wood and published by . This book was released on 1955-06 with total page 534 pages. Available in PDF, EPUB and Kindle. Book excerpt: This is the third edition of a text much loved by engineers and aeronautical engineering students because it relates fundamental aerodynamic concepts to the practical facts of engineering design and teaches the two together. It is the companion to the 10th Edition (1954) of the same author's Airplane Design. This improved reprint has most of the front matter transcribed, all errata corrected, new headers and footers instead of those in the page images, corrected pagination and section references and some improvements in the line art and photographs.
Book Synopsis Static Pressure on Sharp and Blunt Cones in Conical and Parallel Low-density Flow by : Max Kinslow
Download or read book Static Pressure on Sharp and Blunt Cones in Conical and Parallel Low-density Flow written by Max Kinslow and published by . This book was released on 1974 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt: The static pressure distribution on sharp and blunt 10-deg half-angle cones was measured under rarefied conditions in both a uniform and a source flow field. Angle of attack of the cones was varied up to 10 deg. Pressure distributions are presented for cold-wall conditions at 18.0 = or
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 : Langley Aeronautical Laboratory
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.
Book Synopsis Effects of Mach Number and Wall-temperature Ratio on Turbulent Heat Transfer at Mach Numbers from 3 to 5 by : Thorval Tendeland
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 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Velocity Profile, Skin-friction Balance and Heat-transfer Measurements of the Turbulent Boundary Layers at Mach 5 and Zero-pressure Gradient by : Roland E. Lee
Download or read book Velocity Profile, Skin-friction Balance and Heat-transfer Measurements of the Turbulent Boundary Layers at Mach 5 and Zero-pressure Gradient written by Roland E. Lee and published by . This book was released on 1969 with total page 114 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a detailed experimental investigation of a two- dimensional turbulent boundary layer at zero-pressure gradient are presented. The studies were made at the free-stream Mach number of 5, momentum-thickness Reynolds number from 4800 to 56,000 and wall-to-adiabatic-wall temperature ratios from 0.5 to 1.0. The data are in analytical terms of velocity profile, temperature profile, law-of-the-wall, velocity-defect law and incompressible form factor. Comparisons of local skin-friction coefficients obtained by four different experimental methods are shown. An empirical equation was derived from the shear-balance data to calculate the friction coefficient from known values of Mach number, heat transfer and Reynolds number.
Book Synopsis Convective Heat-transfer Rates on a Blunted 110° Cone with Hemispherical Afterbody at Hypersonic Speeds by : David A. Stewart
Download or read book Convective Heat-transfer Rates on a Blunted 110° Cone with Hemispherical Afterbody at Hypersonic Speeds written by David A. Stewart and published by . This book was released on 1971 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements of a Mach 4.9 Zero-pressure-gradient Turbulent Boundary Layer with Heat Yransfer by : Robert L. P. Voisinet
Download or read book Measurements of a Mach 4.9 Zero-pressure-gradient Turbulent Boundary Layer with Heat Yransfer written by Robert L. P. Voisinet and published by . This book was released on 1972 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a detailed experimental investigation of the compressible turbulent boundary layer in a zero-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall for a nominal Mach number of 4.9, at momentum thickness Reynolds numbers from 7,000. to 58,000. and at wall-to-adiabatic-wall temperature ratios of 1.0, 0.8 and 0.25. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. Furthermore, the wall shear and surface heat transfer were measured directly with a skin-friction balance and a heat-transfer gage, respectively. (Author Modified Abstract).
Book Synopsis Hypersonic, Turbulent, Cold-Wall, Skin-Friction and Heat-Transfer Measurements on an Axisymmetric Sharp Cone by : Kuei-Yuan Chien
Download or read book Hypersonic, Turbulent, Cold-Wall, Skin-Friction and Heat-Transfer Measurements on an Axisymmetric Sharp Cone written by Kuei-Yuan Chien and published by . This book was released on 1973 with total page 33 pages. Available in PDF, EPUB and Kindle. Book excerpt: Turbulent skin-friction coefficients directly measured on an axisymmetric five-degree-half-angle sharp cone by two floating-element skin-friction balances at a free-stream Mach number of 7.9 are presented. Heat-transfer distributions are obtained simultaneously. These results yield directly the Reynolds analogy factor. Experimental data are used to evaluate four predictive methods. Except for the relatively low-Reynolds-number case, the directly measured sharp-cone Reynolds analogy factor is between 1.01 and 1.07, which is in good agreement with recent flat-plate measurements. Results indicate that the Stanton Number is essentially constant for one range and decreases by about 10 percent in another. (Modified author abstract).
