Transonic Flow Past A Wedge Profile With Detached Bow Wave
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Transonic Flow Past A Wedge Profile With Detached Bow Wave
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Author : Walter G. Vincenti
language : en
Publisher:
Release Date : 1951
Transonic Flow Past A Wedge Profile With Detached Bow Wave written by Walter G. Vincenti and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with Aerodynamics, Transonic categories.
Numerical calculations have been made of the characteristics at zero angle of attack of a thin, doubly symmetrical, double-wedge profile for the range of supersonic flight speeds in which the bow wave is detached. No special assumptions are made beyond those implicity in the small-disturbance theory of transonic flow. The following results are given as functions of the transonic similarity parameter: (1) shape and location of bow wave and sonic line, (2) chordwise Mach-number and pressure distribution, and (3) integrated pressure drag. The application of the drag results to an airfoil of specific thickness ratio is illustrated.
Transonic Flow Past A Wedge Profile With Detached Bow Wave Details Of Analysis
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Author :
language : en
Publisher:
Release Date : 1951
Transonic Flow Past A Wedge Profile With Detached Bow Wave Details Of Analysis written by and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with categories.
Details are given of calculations of the flow with detached bow wave past a doubly symmetrical, double-wedge profile at zero angle of attack. The results of these calculations have been described previously in NACA TN 2339. The mixed flow over the front of the profile is determined by the solution of a boundary value problem for the transonic small disturbance equation in the hodograph plane. The solution is obtained by the use of finite difference equations and relaxation techniques. The methods follow established lines except for the somewhat novel treatment of the boundary conditions along the shock polar and sonic line. The purely supersonic flow over the rear of the profile is determined by means of the method of characteristics specialized to the transonic small-disturbance theory.
Computation Of The Transonic Flow Over A Wedge With Detached Shock Wave By The Method Of Steepest Descent
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Author : Joseph W. Fischbach
language : en
Publisher:
Release Date : 1953
Computation Of The Transonic Flow Over A Wedge With Detached Shock Wave By The Method Of Steepest Descent written by Joseph W. Fischbach and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with Aerodynamics, Transonic categories.
An Experimental Investigation Of Transonic Flow Past Two Dimensional Wedge And Circular Arc Sections Using A Mach Zehnder Interferometer
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Author : Arthur Earl Bryson
language : en
Publisher:
Release Date : 1951
An Experimental Investigation Of Transonic Flow Past Two Dimensional Wedge And Circular Arc Sections Using A Mach Zehnder Interferometer written by Arthur Earl Bryson and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1951 with Aerodynamic load categories.
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.
Report
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1952
Report written by United States. National Advisory Committee for Aeronautics and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1952 with Aeronautics categories.
Transonic Flow Over A Wedge With A Detached Shock Wave
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Author : Joseph W. Fischbach
language : en
Publisher:
Release Date : 1953
Transonic Flow Over A Wedge With A Detached Shock Wave written by Joseph W. Fischbach and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1953 with categories.
Technical Note National Advisory Committee For Aeronautics
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Author : United States. National Advisory Committee for Aeronautics
language : en
Publisher:
Release Date : 1957
Technical Note National Advisory Committee For Aeronautics written by United States. National Advisory Committee for Aeronautics and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1957 with Aeronautics categories.
General Theory Of Wave Drag Reduction For Combinations Employing Quasi Cylindrical Bodies With An Application To Swept Wing And Body Combinations
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Author : Jack N. Nielsen
language : en
Publisher:
Release Date : 1956
General Theory Of Wave Drag Reduction For Combinations Employing Quasi Cylindrical Bodies With An Application To Swept Wing And Body Combinations written by Jack N. Nielsen and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1956 with Airplanes categories.
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.
General Theory Of High Speed Aerodynamics
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Author : William Rees Sears
language : en
Publisher: Princeton University Press
Release Date : 2015-12-08
General Theory Of High Speed Aerodynamics written by William Rees Sears and has been published by Princeton University Press this book supported file pdf, txt, epub, kindle and other format this book has been release on 2015-12-08 with Science categories.
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.
Theoretical And Analog Studies Of The Effects Of Nonlinear Stability Derivatives On The Longitudinal Motions Of An Aircraft In Response To Step Control Deflections And To The Influence Of Proportional Automatic Control
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Author : Benjamin Milwitzky
language : en
Publisher:
Release Date : 1955
Theoretical And Analog Studies Of The Effects Of Nonlinear Stability Derivatives On The Longitudinal Motions Of An Aircraft In Response To Step Control Deflections And To The Influence Of Proportional Automatic Control written by Benjamin Milwitzky and has been published by this book supported file pdf, txt, epub, kindle and other format this book has been release on 1955 with Aeronautics categories.