## An Introduction to Theoretical and Computational AerodynamicsThis concise and highly readable introduction to theoretical and computational aerodynamics integrates both classical and modern developments, focusing on applying methods to actual wing design. Designed for a junior- or senior-level course and as a resource for practicing engineers, it features 221 figures. 1984 edition. |

### What people are saying - Write a review

User Review - Flag as inappropriate

Why would I write a review of a book where I only have access to a part of it. Get serious people. I happen to have the hard copy of this book and would like to be able to copy the fortran programs from an ocr.

### Contents

WINGS | 1 |

REVIEW OF BASIC FLUID DYNAMICS | 11 |

INCOMPRESSIBLE IRROTATIONAL FLOW ABOUT | 32 |

LIFTING AIRFOILS IN INCOMPRESSIBLE IRROTATIONAL 60 | 80 |

WINGS OF FINITE SPAN | 124 |

THE NAVIERSTOKES EQUATIONS | 154 |

THE BOUNDARY LAYER | 191 |

PANEL METHODS 26 | 260 |

FINITE DIFFERENCE METHODS | 289 |

10 FINITEDIFFERENCE SOLUTION OF THE BOUNDARY | 335 |

COMPRESSIBLE POTENTIAL FLOW PAST AIRFOILS | 381 |

APPENDIX A An Important Integral | 424 |

Uniqueness of Solutions of Laplace Equation | 433 |

APPENDIX G Geometrical Demonstration That Strain is | 446 |

Structure of a Weak Shock Wave | 456 |

### Common terms and phrases

aerodynamic airfoil angle of attack axis Bernoulli's equation body surface boundary conditions boundary layer calculated called camber Chapter chord circulation compute constant continuity equation convergence coordinates defined derivatives difference differential equation direction doublet distribution ellipse evaluate finite-difference approximation finite-difference equations finite-difference method flow past fluid particle force formula heat equation incompressible induced drag INPUT integral equation inviscid irrotational iterations Kutta condition laminar Laplace equation leading edge lift coefficient linear Mach number mesh molecules momentum NACA Navier-Stokes equations no-slip condition nodes normal obtained onset flow panel method plane pressure distribution pressure gradient PRINT problem RETURN END Reynolds number satisfy shear stress shown in Fig solution solve source distribution source strength stagnation point stream function streamline SUBROUTINE supersonic tangential thin-airfoil theory trailing edge transonic two-dimensional upstream vector velocity components velocity field velocity potential velocity profile viscous vortex strength vortices wing zero