Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Theoretical Distribution Of Load Over A Swept Back Wing
Download Theoretical Distribution Of Load Over A Swept Back Wing full books in PDF, epub, and Kindle. Read online Theoretical Distribution Of Load Over A Swept Back Wing ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Theoretical Distribution of Load Over a Swept-back Wing by : Doris Cohen
Download or read book Theoretical Distribution of Load Over a Swept-back Wing written by Doris Cohen and published by . This book was released on 1942 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: The load over an elliptical wing with 30 degrees sweepback has been calculated by a method, based on vortex theory, which takes account of the chordwise distribution of lifting area. The theory indicates a 14-percent loss in total lift due to the introduction of sweepback, with the greatest loss taking place at the center of the span. An increase in concentration of load at the tips is also indicated. The results are compared with the results previously obtained by somewhat simpler calculations based on the assumption of a single lifting vortex.
Book Synopsis Theoretical Loading at Supersonic Speeds of Flat Swept-back Wings with Interacting Trailing and Leading Edges by : Doris Cohen
Download or read book Theoretical Loading at Supersonic Speeds of Flat Swept-back Wings with Interacting Trailing and Leading Edges written by Doris Cohen and published by . This book was released on 1949 with total page 64 pages. Available in PDF, EPUB and Kindle. Book excerpt: By the method of superposition of conical flows, the load distribution is calculated for regions of a long swept-back wing behind the points at which the Mach lines from the trailing-edge apex intersect the leading edge. It is found that a good approximation on the load can be obtained by the application of a fairly simple correction factor to the two-dimensional subsonic distribution. The similarity of two-dimensional flow is used to derive expressions for the loss of lift behind the Mach lines from the tips of the wing.
Book Synopsis Linearized Lifting-surface Theory for Swept-back Wings with Slender Plan Forms by : Harvard Lomax
Download or read book Linearized Lifting-surface Theory for Swept-back Wings with Slender Plan Forms written by Harvard Lomax and published by . This book was released on 1949 with total page 48 pages. Available in PDF, EPUB and Kindle. Book excerpt: The spanwise and chordwise distribution of loading, the lift, and the induced drag of a swept-back wing of slender plan form are developed by means of linearized lifting-surface theory. The results are applicable for all free-stream Mach numbers. The term slender implies that the ratio of the reduced span to over-all length of the wing is small.
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 290 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Wing Load Distribution on a Swept-wing Airplane in Flight at Mach Numbers Up to 1.11, and Comparison with Theory by : L. Stewart Rolls
Download or read book Wing Load Distribution on a Swept-wing Airplane in Flight at Mach Numbers Up to 1.11, and Comparison with Theory written by L. Stewart Rolls and published by . This book was released on 1952 with total page 73 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 1943 with total page 902 pages. Available in PDF, EPUB and Kindle. Book excerpt: Reproductions of reports, some declassified, of research done at Langley Memorial Aeronautical Laboratory during World War II. The order of reports does not represent when they were chronologically issued. Reference to the original version of each report is included.
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 646 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 1950 with total page 988 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 The Calculation of Span Load Distributions on Swept-back Wings by : William Mutterperl
Download or read book The Calculation of Span Load Distributions on Swept-back Wings written by William Mutterperl and published by . This book was released on 1941 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Span load distributions of swept-back wings have been calculated. The method used was to replace the wing with a bound vortex at the quarter-chord line and to calculate the downwash due to the system of bound and trailing vortices to conform at the three-quarter-chord line to the slope of the flat-plate wing surface. Results are given for constant-chord and 5:1 tapered plan forms, for swee-pback angles of 0, 30 and 45 degresss, and for aspect ratios of 3, 6, and 9. Some comments on the stalling of swept-back wings are included.
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 1954 with total page 994 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Use of Source Distributions for Evaluating Theoretical Aerodynamics of Thin Finite Wings at Supersonic Speeds by : A. J. Eggers
Download or read book Use of Source Distributions for Evaluating Theoretical Aerodynamics of Thin Finite Wings at Supersonic Speeds written by A. J. Eggers and published by . This book was released on 1950 with total page 264 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis High Speed Wing Theory by : Doris Cohen
Download or read book High Speed Wing Theory written by Doris Cohen and published by Princeton University Press. This book was released on 2015-12-08 with total page 251 pages. Available in PDF, EPUB and Kindle. Book excerpt: Part of the Princeton Aeronautical Paperback series designed to bring to students and research engineers outstanding portions of the twelve-volume High Speed Aerodynamics and Jet Propulsion series. These books have been prepared by direct reproduction of the text from the original series and no attempt has been made to provide introductory material or to eliminate cross reference to other portions of the original volumes. Originally published in 1960. The Princeton Legacy Library uses the latest print-on-demand technology to again make available previously out-of-print books from the distinguished backlist of Princeton University Press. These editions preserve the original texts of these important books while presenting them in durable paperback and hardcover editions. The goal of the Princeton Legacy Library is to vastly increase access to the rich scholarly heritage found in the thousands of books published by Princeton University Press since its founding in 1905.
Book Synopsis A Comparison of Three Theoretical Methods of Calculating Span Load Distribution on Swept Wings by : Nicholas H. Van Dorn
Download or read book A Comparison of Three Theoretical Methods of Calculating Span Load Distribution on Swept Wings written by Nicholas H. Van Dorn and published by . This book was released on 1947 with total page 77 pages. Available in PDF, EPUB and Kindle. Book excerpt: It was found that (1) the Weissinger method gave good accuracy and involved by far the least computing effort and (2) the Falkner method gave the best accuracy but at considerable expense in computing effort.
Book Synopsis Monthly Catalog of United States Government Publications, Cumulative Index by : United States. Superintendent of Documents
Download or read book Monthly Catalog of United States Government Publications, Cumulative Index written by United States. Superintendent of Documents and published by . This book was released on 1968 with total page 1366 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis United States Government Publications Monthly Catalog by :
Download or read book United States Government Publications Monthly Catalog written by and published by . This book was released on 1946 with total page 1572 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Theoretical Span Load Distributions and Rolling Moments for Sideslipping Wings of Arbitrary Plan Form in Incompressible Flow by : M. J. Queijo
Download or read book Theoretical Span Load Distributions and Rolling Moments for Sideslipping Wings of Arbitrary Plan Form in Incompressible Flow written by M. J. Queijo and published by . This book was released on 1955 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt: A method of computing span loads and the resulting rolling moments for sideslipping wings of arbitrary plan form in incompressible flow is derived. The method requires that the span load at zero sideslip be known for the wing under consideration. Because this information is available for a variety of wings, this requirement should not seriously restrict the application of the present method. The basic method derived herein requires a mechanical differentiation and integration to obtain the rolling moment for the general wing in sideslip. For wings having straight leading and trailing edges over each semispan, the rolling moment equation in terms of plan-form parameters and the lateral center of pressure of the lift due to angle of attack. Calculated span loads and rolling-moment parameters are compared with experimental values. The comparison indicates good agreement between calculations and available experimental data.
