Chordwise And Compressibility Corrections To Slender Wing Theory PDF Download
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| Author | : Harvard Lomax |
| Publisher | : |
| Total Pages | : 50 |
| Release | : 1951 |
| Genre | : Aerodynamic load |
| ISBN | : |
Download Chordwise and Compressibility Corrections to Slender-wing Theory Book in PDF, ePub and Kindle
Corrections to slender-wing theory are obtained by assuming a spanwise distribution of loading and determining the chordwise variation which satisfies the appropriate integral equation. Such integral equations are set up in terms of the given vertical induced velocity on the center line, or depending on the type of wing plan form, its average value across the span at a given chord station. The chordwise distribution is then obtained by solving these integral equations. Results are shown for flat-plate, rectangular, and triangular wings.
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 30 |
| Release | : 1952 |
| Genre | : Aeronautics |
| ISBN | : |
Download Report Book in PDF, ePub and Kindle
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 1200 |
| Release | : 1954 |
| Genre | : Aeronautics |
| ISBN | : |
Download Annual Report of the National Advisory Committee for Aeronautics Book in PDF, ePub and Kindle
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
| Author | : Antonio Ferri |
| Publisher | : |
| Total Pages | : 346 |
| Release | : 1952 |
| Genre | : Aerodynamic load |
| ISBN | : |
Download An Empirically Derived Basis for Calculating the Area, Rate, and Distribution of Water-drop Impingement on Airfoils Book in PDF, ePub and Kindle
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 664 |
| Release | : 1948 |
| Genre | : Aeronautics |
| ISBN | : |
Download Report - National Advisory Committee for Aeronautics Book in PDF, ePub and Kindle
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 542 |
| Release | : 1953 |
| Genre | : Aeronautics |
| ISBN | : |
Download Technical Note - National Advisory Committee for Aeronautics Book in PDF, ePub and Kindle
| Author | : James C. Sivells |
| Publisher | : |
| Total Pages | : 722 |
| Release | : 1951 |
| Genre | : Ailerons |
| ISBN | : |
Download Method for Calculating Lift Distribtutions for Unswept Wings with Flaps Or Ailerons by Use of Nonlinear Section Lift Data Book in PDF, ePub and Kindle
A method is presented for calculating lift distributions for unswept wings with flaps or ailerons using nonlinear section lift data. This method is based upon lifting-line theory and is an extension to the method described by NACA Report 865. Simplified computing forms containing detailed examples are given for both symmetrical and asymmetrical lift distributions. A few comparisons of experimental and calculated characteristics are also presented.
| Author | : |
| Publisher | : |
| Total Pages | : 146 |
| Release | : 1971 |
| Genre | : Aeronautics |
| ISBN | : |
Download NASA Technical Memorandum Book in PDF, ePub and Kindle
| Author | : Rudolph W. Hensel |
| Publisher | : |
| Total Pages | : 708 |
| Release | : 1951 |
| Genre | : Mathematical analysis |
| ISBN | : |
Download Rectangular-wind-tunnel Blocking Corrections Using the Velocity-ratio Method Book in PDF, ePub and Kindle
Calculations of the ratios of the velocity increments at test bodies to those at the tunnel walls caused by the solid blocking of these bodies within the walls of a closed rectangular wind tunnel are presented. The boides treated include two-dimensional airfoils; small bodies of revolution; straight, untapered, finite-span wings of varying span; and swept, untapered, finite-span wings of varying span. It is shown that, after wake blocking effects have been removed , the present method furnishes semiempirical blocking corrections for most wind-tunnel models and their components. The test section proportions of the Southern California Cooperative Wind Tunnel at CIT (ratio of height to width equal to 1/square root of 2) are used in the calculations.
| Author | : |
| Publisher | : CUP Archive |
| Total Pages | : 268 |
| Release | : |
| Genre | : |
| ISBN | : |
Download linearized theory of steady high-speed flow Book in PDF, ePub and Kindle
