## Unsteady Transonic FlowFirst published in 1961 this monograph deals with the analysis of unsteady lift distributions of thin oscillating wings at transonic speeds. Such distributions are needed for the prediction of flutter, which tends to occur more frequently at speeds near that of sound than in any other speed regime. This book emphasises analytical methods that treat the linearised problem for simple wing planforms such as rectangular and delta wings. There is a thorough discussion of the limitations of the validity of linearised theory as well as the proper boundary conditions to be applied for the case of flows with shocks. Although the standard approach in engineering practice is to sense transonic flow calculations with the aid of direct numerical simulations on a high-speed computer, the treatment in this classic monograph is still of value in the physical insight it provides and in the reference 'exact' solutions it supplies for simplified cases that may serve as validation cases for complicated computer codes. This classic work will be of interest to aerodynamicists, fluid dynamicists and applied mathematicians. |

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### Contents

TWODIMENSIONAL SOLUTION | 24 |

LOW ASPECT RATIO WINGS OF TRIANGULAR | 32 |

THE LOW ASPECT RATIO RECTANGULAR WING | 41 |

LOW ASPECT RATIO WINGBODY COMBINATIONS | 55 |

THE RECTANGULAR WING OF ARBITRARY ASPECT | 76 |

THE DELTA WING OF ARBITRARY ASPECT RATIO | 91 |

WINGS OF GENERAL PLANFORMS | 99 |

CONTROL SURFACE BUZZ | 110 |

EXPERIMENTAL DETERMINATION OF AIR FORCES | 123 |

Author Index | 131 |

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### Common terms and phrases

Aero aerodynamic aerodynamic forces airfoil amplitude approximation aspect ratio theory Aspect Ratio Wings assume asymptotic boundary conditions boundary value problem buzz calculation cancel chord Concave polygonal considered control surface converges delta wing denote differential equation due to translation Eckhaus effects exponential terms finite first-order flutter forces and moments Fourier transformed given by Eq gives Hence higher order terms hinge Kutta condition Landahl large values leading edge linearized theory low aspect ratio Mach number Mathieu functions Miles Ref NACA neglected non-linear normal derivative obtained oscillating wing perturbation velocities pitching oscillations planform pressure coefficient pressure distribution receding wave reduced frequency shown in Fig side edge solution of Eq sonic stability derivatives strip theory subsonic supersonic Supersonic Flow tangency condition theory of Chapter three-dimensional trailing edge transonic region transonic speeds transonic theory two-dimensional unsteady flow unsteady transonic flow valid velocity potential wake Wing-Body Combinations zero