Author: David Harry LeePublisher:
ISBN:
Category :
Languages : en
Pages :
Book Description
A Second Order Theory for Supersonic Flow Over Three-dimensional Wings
A second-order theory for three-dimensional wings in supersonic flow
Author: Mark Hall ClarksonPublisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 128
Book Description
On 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).
Second-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).
A Second Order Supersonic Theory for Three-dimensional Wings
Author: D. H. LeeSecond-Order Theory of Optimum Two-Dimensional Wings in Supersonic Flow Including the Effects of Friction
Author: Angelo MieleA 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
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
Supersonic Flow Past Finite Double Wedge Wings of Variable Thickness
Author: Maurice HoltPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 86
Book Description
In this case the whole disturbed flow field also varies sinusoidally with span. In region (i) the pressure satisfies the telegraph equation and the problem of calculating the disturbed flow field reduces to an integro-differential-difference equation for the distorted shock shape function. The solution of this equation, the existence and uniqueness of which is established, is obtained in the form of series expansions in chordwise distance on the shock ... In region (ii) the surface pressure satisfies a Volterra integral equation which can be solved by a simple numerical procedure. The present paper takes no account of edge effects, which must be treated separately as a conefield problem.
The Calculation of Three-dimensional Supersonic Flows Around Spherically-capped Smooth Bodies and Wings: Theory and applications
Author: Chong-Wei ChuPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 92
Book Description