Recent Advances in Boundary Layer Theory


Book Description

Dedicated to Prof. W.Schneider on the Occasion of his 60th Birthday




Boundary-Layer Theory


Book Description

This new edition of the near-legendary textbook by Schlichting and revised by Gersten presents a comprehensive overview of boundary-layer theory and its application to all areas of fluid mechanics, with particular emphasis on the flow past bodies (e.g. aircraft aerodynamics). The new edition features an updated reference list and over 100 additional changes throughout the book, reflecting the latest advances on the subject.







Fluid Mechanics for Engineers


Book Description

The contents of this book covers the material required in the Fluid Mechanics Graduate Core Course (MEEN-621) and in Advanced Fluid Mechanics, a Ph. D-level elective course (MEEN-622), both of which I have been teaching at Texas A&M University for the past two decades. While there are numerous undergraduate fluid mechanics texts on the market for engineering students and instructors to choose from, there are only limited texts that comprehensively address the particular needs of graduate engineering fluid mechanics courses. To complement the lecture materials, the instructors more often recommend several texts, each of which treats special topics of fluid mechanics. This circumstance and the need to have a textbook that covers the materials needed in the above courses gave the impetus to provide the graduate engineering community with a coherent textbook that comprehensively addresses their needs for an advanced fluid mechanics text. Although this text book is primarily aimed at mechanical engineering students, it is equally suitable for aerospace engineering, civil engineering, other engineering disciplines, and especially those practicing professionals who perform CFD-simulation on a routine basis and would like to know more about the underlying physics of the commercial codes they use. Furthermore, it is suitable for self study, provided that the reader has a sufficient knowledge of calculus and differential equations. In the past, because of the lack of advanced computational capability, the subject of fluid mechanics was artificially subdivided into inviscid, viscous (laminar, turbulent), incompressible, compressible, subsonic, supersonic and hypersonic flows.







Boundary-Layer Theory


Book Description

A new edition of the almost legendary textbook by Schlichting completely revised by Klaus Gersten is now available. This book presents a comprehensive overview of boundary-layer theory and its application to all areas of fluid mechanics, with emphasis on the flow past bodies (e.g. aircraft aerodynamics). It contains the latest knowledge of the subject based on a thorough review of the literature over the past 15 years. Yet again, it will be an indispensable source of inexhaustible information for students of fluid mechanics and engineers alike.




General Theory of Wave-drag Reduction for Combinations Employing Quasi-cylindrical Bodies with an Application to Swept-wing and Body Combinations


Book Description

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.







A Nonlinear Theory for Predicting the Effects of Unsteady Laminar, Turbulent, Or Transitional Boundary Layers on the Attenuation of Shock Waves in a Shock Tube with Experimental Comparison


Book Description

Summary: The linearized attenuation theory of NACA Technical Note 3375 is modified in the following manner: (a) an unsteady compressible local skin-friction coefficient is employed rather than the equivalent steady-flow incompressible coefficient; (b) a nonlinear approach is used to permit application of the theory to large attenuations; and (c) transition effects are considered. Curves are presented for predicting attenuation for shock pressure ratios up to 20 and a range of shock-tube Reynolds numbers. Comparison of theory and experimental data for shock-wave strengths between 1.5 and 10 over a wide range of Reynolds numbers shows good agreement with the nonlinear theory evaluated for a transition Reynolds number of 2.5 x 106.