Author: Mark Hall ClarksonPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 128
Book Description
A second-order theory for three-dimensional wings in supersonic flow
Author: Mark Hall ClarksonPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 128
Book Description
A Second Order Theory for Supersonic Flow Over Three-dimensional Wings
Author: David Harry LeeA Second Order Supersonic Theory for Three-dimensional Wings
Author: D. H. LeeOn the Calculation of Unsteady Nonlinear Three-dimensional Supersonic Flow Past Wings
Author: Stanford University. Department of Aeronautics and AstronauticsPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 106
Book Description
A comprehensive study is made of factors influencing the accuracy of predicted thickness effects on the flow due to oscillatory motion of a sweptback wing in supersonic flight. For a delta planform with its leading edge swept at or near the Mach angle, the streamlines and velocity pattern due to thickness are found to be highly three-dimensional. Based on this observation, improvements are suggested to previous approximate second-order theories for the unsteady loading. Numerical examples are presented for 45 degree delta wings of 5% and 10% thicknesses, which indicate a substantial difference between the linearized and nonlinear lifting potential distributions. Although a greater volume of computation is needed to guarantee adequate accuracy, practical means are described for the complete numerical solution of problems of this type. (Author).
A Second Order Slender Wing Theory for Wings with Leading Edge Separation in Supersonic Flow
Author: Joseph P. NenniPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 76
Book Description
Second-Order Theory of Optimum Two-Dimensional Wings in Supersonic Flow Including the Effects of Friction
Author: Angelo MieleSecond-Order Theory for a Thin Wing in Supersonic Flow with a Weak Spanwise Entropy Gradients
Author: PETER G. WILBYPublisher:
ISBN:
Category :
Languages : en
Pages : 1
Book Description
The three-dimensional perturbation velocities over an infinite thin wing with a sharp leading edge in non-uniform supersonic flow are derived and used to investigate the second-order contribution to the pressure coefficient on a wing surface, due to a spanwise entropy gradient. Pressure distributions are calculated for a wedge section wing at various Mach numbers for probable values of entropy gradient. Results show that entropy gradient effects can be important. Procedure for application of the theory is given for the case of a wing situated behind the curved shock generated by a blunt nosed body. (Author).
Wing Theory
Author: A. RobinsonPublisher: Cambridge University Press
ISBN: 1107622654
Category : Technology & Engineering
Languages : en
Pages : 583
Book Description
First published in 1956 as part of the Cambridge Aeronautical Series, this book addresses the vital science of wing theory. Robinson and Laurmann record the historic developments in wing theory, including the work of Joukowski and Bernoulli, and discuss developments in supersonic flow and unsteady aerofoil theory. This book will be of value to anyone with an interest in the history of the science of flight.
Technical Note - National Advisory Committee for Aeronautics
Author: United States. National Advisory Committee for AeronauticsPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1304
Book Description
Theoretical Investigation and Application of Transonic Similarity Law for Two Dimensional Flow
Author: William PerlPublisher:
ISBN:
Category : Air flow
Languages : en
Pages : 724
Book Description
The transonic similarity law for two-dimensional flow derived by von Karman was investigated by an iteration procedure similar to that of the Rayleigh-Janzen and Ackeret-Prandtl-Glauert methods. The results, which show that the potential can be expressed as a power series in a single parameter that depends on Mach number, thickness ratio, and ratio of specific heats, are in agreement with those of von Karman. By the iteration procedure, the second approximation for the flow past a Kaplan section was obtained in similarity form. The exact solution by Kaplan for the second approximation was examined and found expressible in the same similarity form. The exact numerical results to three approximations obtained by Kaplan for the Kaplan section and the circular arc have been reduced to transonic similarity form.