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Investigation Of The Variation Of Lift Coefficient With Reynolds Number At A Moderate Angle Of Attack On A Low Drag Airfoil
Download Investigation Of The Variation Of Lift Coefficient With Reynolds Number At A Moderate Angle Of Attack On A Low Drag Airfoil full books in PDF, epub, and Kindle. Read online Investigation Of The Variation Of Lift Coefficient With Reynolds Number At A Moderate Angle Of Attack On A Low Drag Airfoil ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Experimental Investigation of a 90 Degree Cascade Diffusing Bend with an Area Ratio of 1.45:1 and with Several Inlet Boundary Layers by : Daniel Friedman
Download or read book Experimental Investigation of a 90 Degree Cascade Diffusing Bend with an Area Ratio of 1.45:1 and with Several Inlet Boundary Layers written by Daniel Friedman and published by . This book was released on 1952 with total page 804 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation was conducted in order to determine the performance of a 90 degree cascade diffusing bend with an area ratio of 1.45:1 and a 19-inch square inlet with several inlet-boundary-layer shapes and thicknesses. The maximum mean inlet Mach number was 0.41 and the corresponding airfoil Reynolds number was 950,000. The experimental results seem to indicate that, when the duct configuration requires a bend, a certain amount of diffusion can be obtained without an appreciable rise in the total-pressure losses. If length is important, this configuration requires much less space than the usual diffuser-bend combination.
Book Synopsis An Experimental Investigation of Regions of Separated Laminar Flow by : Donald E. Gault
Download or read book An Experimental Investigation of Regions of Separated Laminar Flow written by Donald E. Gault and published by . This book was released on 1955 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt: Results are presented from an investigation of regions of separated flow caused by separation of the laminar boundary layer (laminar-separation "bubbles"). The investigation was undertaken to obtain measurements which would define a large number of these bubbles for a wide range of Reynolds numbers and pressure gradients. In this manner, existing physical interpretations of the flow along a bubble could be studied in greater detail than in the past and, at the same time, it was hoped that the data would provide further insight into the conditions which control the occurrence and extent of a bubble.
Book Synopsis NACA Wartime Report by : United States. National Advisory Committee for Aeronautics
Download or read book NACA Wartime Report written by United States. National Advisory Committee for Aeronautics and published by . This book was released on with total page 764 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Wartime Report written by and published by . This book was released on 1941 with total page 236 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wartime Report by : United States. National Advisory Committee for Aeronautics
Download or read book Wartime Report written by United States. National Advisory Committee for Aeronautics and published by . This book was released on with total page 516 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Progress in Aeronautical Sciences by : D. Küchemann
Download or read book Progress in Aeronautical Sciences written by D. Küchemann and published by Elsevier. This book was released on 2016-07-04 with total page 327 pages. Available in PDF, EPUB and Kindle. Book excerpt: Progress in Aeronautical Sciences, Volume 5, contains six articles that belong to the field of aerodynamics. This accords well with one of the declared purposes of this series, to serve the general reader with accounts of those parts of the subject remote from his specialized interest, not only because his field of specialization is likely to change during his career but also because we are all students of one science. The first paper gives a comprehensive survey of low-speed wind-tunnels, those early tools of the aerodynamicist which seem likely to retain their importance indefinitely. The second deals with a basic feature of the separation of a laminar boundary layer from a wall in two-dimensional flow: the bubble. The third reports on the more theoretical aspects of the IUTAM Symposium Transsonicum, which afforded a reunion of almost everyone who at one time or another had contributed to our knowledge of flows of mixed type. The fourth paper is concerned with a particular aspect of the theory of transonic flows and gives an exhaustive survey of this work. The fifth paper reports on a symposium devoted to rarefied gas dynamics. The final paper presents corrections to an article on the theory of sonic bangs, published in Volume 1 of this series.
Book Synopsis The Application of Green's Theorem to the Solution of Boundary-value Problems in Linearized Supersonic Wing Theory by : Max A. Heaslet
Download or read book The Application of Green's Theorem to the Solution of Boundary-value Problems in Linearized Supersonic Wing Theory written by Max A. Heaslet and published by . This book was released on 1949 with total page 656 pages. Available in PDF, EPUB and Kindle. Book excerpt: Under the assumptions of linearized theory, general methods of solutin are given for two- and three-dimensional steady-state and two-dimensional unsteady-state equations of compressible flow. The solutions depend in all cases on the use of Green's equivalent layer of sources, sinks, and doublets. Emphasis is placed on applications in supersonic wing theory, the singularities arising in the integrations being treated by Hadamard's finite part of the technique. Four examples of different character are discussed. In particular, the load distribution over a specific swept-back lifting surface is determined at a free-stream Mach number of one.
Book Synopsis Technical Note by : United States. National Advisory Committee for Aeronautics
Download or read book Technical Note written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1947 with total page 446 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Technical Note - National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics
Download or read book Technical Note - National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1955 with total page 1276 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Calculation of Downwash Behind Supersonic Wings with an Application to Triangular Plan Forms by : Max A. Heaslet
Download or read book The Calculation of Downwash Behind Supersonic Wings with an Application to Triangular Plan Forms written by Max A. Heaslet and published by . This book was released on 1948 with total page 726 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method is developed, consistent with the assumptions of small perturbation theory, which provides a means of determining for a known load distribution, the downwash behind a wing in supersonic flow. THe analysis is based upon the use of supersonic doublets which are distributed over the plan form and wake of the wing in a manner determined from the wing loading.
Book Synopsis A Scale and Turbulence Effects on the Lift and Drag Characteristics of the NACA 653-418 by : John H. Quinn
Download or read book A Scale and Turbulence Effects on the Lift and Drag Characteristics of the NACA 653-418 written by John H. Quinn and published by . This book was released on 1944 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Summary: An investigation in two NACA wind tunnels has determined the effect of Reynolds number and stream turbulence on the lift and drag characteristics of a low-drag airfoil, the NACA 653-418, a=1.0 section, particularly at low Reynolds numbers, to give an indication of the performance of low-drag wings in low-scale tests. The results are correlated with similar data for the same airfoil section in the NACA two-dimensional low-turbulence pressure tunnel to provide data over a range of Reynolds number from 0.19 to 9.0 x 106. Large increases in minimum drag coefficient were found as the Reynolds number decreased. This effect was particularly marked at Reynolds numbers below 1.5 x 106. At Reynolds numbers below 1.5 x 106, stream turbulence had little effect on the drag characteristics of the NACA 653-418 airfoil section when compared on the basis of test Reynolds number but, at higher Reynolds numbers, stream turbulence had a detrimental effect on drag. Large decreases in maximum lift coefficient were found with decreasing Reynolds number; most of this decrease was encountered at Reynolds numbers above 2.0 x 106. Marked differences in maximum lift were apparent between the results obtained at high and low turbulence. When compared on the basis of effective Reynolds number, however, fair agreement was reached between the data obtained under both turbulence conditions.
Book Synopsis A Systematic Investigation of Pressure Distributions at High Speeds Over Five Representative NACA Low-drag and Conventional Airfoil Sections by : Carl Kaplan
Download or read book A Systematic Investigation of Pressure Distributions at High Speeds Over Five Representative NACA Low-drag and Conventional Airfoil Sections written by Carl Kaplan and published by . This book was released on 1945 with total page 238 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Spanwise Distribution of Lift for Minimum Induced Drag of Wings Having a Given Lift and a Given Bending Moment by : Robert T. Jones
Download or read book The Spanwise Distribution of Lift for Minimum Induced Drag of Wings Having a Given Lift and a Given Bending Moment written by Robert T. Jones and published by . This book was released on 1950 with total page 708 pages. Available in PDF, EPUB and Kindle. Book excerpt: The problem of the minimum induced drag of wings having a given lift and a given span is extended to include cases in which the bending moment to be supported by the wing is also given. Expressions for the spanwise load distribution and the minimum drag in terms of the lateral position of the load centroid are given. The results show a 15-percent reduction of the induced drag with a 15-percent increase in span over that for an elliptic loading having the same total lift and bending moment.
Download or read book Report written by and published by . This book was released on 1957 with total page 1180 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis NACA Conference on Boundary Layers by : United States. National Advisory Committee for Aeronautics
Download or read book NACA Conference on Boundary Layers written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1947 with total page 196 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Annual Report - National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics
Download or read book Annual Report - National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1957 with total page 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 Report - National Advisory Committee for Aeronautics by : United States. National Advisory Committee for Aeronautics
Download or read book Report - National Advisory Committee for Aeronautics written by United States. National Advisory Committee for Aeronautics and published by . This book was released on 1939 with total page 780 pages. Available in PDF, EPUB and Kindle. Book excerpt:
