Transonic Flow Past A Wedge Profile With Detached Bow Wave
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| Author | : Arthur Earl Bryson |
| Publisher | : |
| Total Pages | : 106 |
| Release | : 1951 |
| Genre | : Aerodynamic load |
| ISBN | : |
Interferometer measurements are given of the flow fields near two-dimensional wedge and circular-arc sections at zero angle of attack. Pressure distributions and drag coefficients as functions of Mach number were obtained and the wedge data are compared with theory. It is shown that the local Mach number at any point on the surface of a finite three dimensional body or an unswept two-dimensional body, moving through an infinite fluid, has a stationary value at Mach number 1 and, in fact, remains nearly constant for a range of speeds below and above Mach number 1. On the basis of this concept and the experimental data, pressure distributions and drag coefficients for the wedge and circular-arc sections are presented throughout the entire transonic range of velocities.
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 988 |
| Release | : 1957 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1958 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : Jack N. Nielsen |
| Publisher | : |
| Total Pages | : 676 |
| Release | : 1956 |
| Genre | : Airplanes |
| ISBN | : |
The wing-body interference theory of NACA TN 2677 applied to symmetrical wings in combination with quasi-cylindrical bodies permits the direct calculation of pressure-distribution changes produced by body shape changes. This theory is used to determine the relative magnitued of the wave-drag reduction produced by changes in cylinder cross-sectional area and that produced changes in cross-sectional shape (without change in area). The body distortion is expressed as a Fourier series, and an integral equation is derived for the body shape for minimum drag for each Fourier component. Thus the wave-drag reductions for the various Fourier harmonics are independent and additive.
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : |
| Release | : 1955 |
| Genre | : Aeronautics |
| ISBN | : |
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
| Author | : William Rees Sears |
| Publisher | : Princeton University Press |
| Total Pages | : 778 |
| Release | : 2015-12-08 |
| Genre | : Science |
| ISBN | : 1400877555 |
Volume VI of the High Speed Aerodynamics and Jet Propulsion series. This volume includes: physical and mathematical aspects of high speed flows; small perturbation theory; supersonic and transonic small perturbation theory; higher order approximations; nonlinear subsonic and transonic flow theory; nonlinear supersonic steady-flow theory; characteristic methods; flows with shock waves. Originally published in 1954. 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.
| Author | : Benjamin Milwitzky |
| Publisher | : |
| Total Pages | : 348 |
| Release | : 1955 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 512 |
| Release | : 1951 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : United States. National Advisory Committee for Aeronautics |
| Publisher | : |
| Total Pages | : 568 |
| Release | : 1951 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : E. Epremian |
| Publisher | : |
| Total Pages | : 746 |
| Release | : 1952 |
| Genre | : Iron |
| ISBN | : |
Extensive fatigue tests were made on annealed Armco iron and plain carbon and alloy steels heat-treated to different strengths and microstructures. Statistics of fatigue-fracture curves and endurance limits were determined from the experimental data obtained and, for various other materials, from a survey of literature. The results were analyzed to show the relative effects of various metallurgical factors on the statistical nature of fatigue properties. Other phases of the problem studied include: dependence of statistical variation in fatigue life on stress level in the fracture range, statistics for location of crack initiation, size effect, understressing effect, and the form and method of plotting the S-N diagram.
