By Tuncer Cebeci, Jean Cousteix
This moment version of our e-book extends the modeling and calculation of boundary-layer flows to incorporate compressible flows. the topics hide laminar, transitional and turbulent boundary layers for 2- and third-dimensional incompressible and compressible flows. The viscous-inviscid coupling among the boundary layer and the inviscid circulation can be addressed. The e-book has a great number of homework problems.
Read Online or Download Modeling and Computation of Boundary-Layer Flows: Laminar, Turbulent and Transitional Boundary Layers in Incompressible and Compressible Flows PDF
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Extra info for Modeling and Computation of Boundary-Layer Flows: Laminar, Turbulent and Transitional Boundary Layers in Incompressible and Compressible Flows
Introduction 16 (CL):, TEST DATA - PRESSURE DIFFERENCE RULE 2 4 6 8 10 12 14 16 R xlO"^ Fig. 15. Variation of maximum lift coefficient with Reynolds number based on mean aerodynamic chord, Ra. Reynolds number is considerable, and the method based on the Pressure Difference Rule captures it remarkably well. References  Bushnell, D. M. : Viscous Drag Reduction, AIAA "Progress in Aeronautics and Astronautics" Series, 1989. : "The Problem of Three-Dimensional Lifting Flow and Its Solution by Means of Surface Singularity Distribution," Computer Methods in Applied Mechanics and Engineering 4, 283-319, 1974.
Coo) = i Here the primes denote differentiation with respect to C,. When /? is infinite, Eq. 34) A closed form solution to Eqs.
19b) numerically. Before we discuss the numerical solutions of Eqs. 8) for various values of m, it is useful to single out two flows that are quite common in practice. The first one corresponds to m = 0 (/? = 0) and is the flow over a flat plate at zero incidence. In this case, the external velocity, Ue^ is constant, and Eq. 20) This equation is called the Blasius equation. The second flow corresponds to m = 1 (/? = 1, wedge half-angle 90°), which is the case of a two-dimensional stagnation flow.