Development of an advanced panel method for complex configurations in subsonic compressible flow; Application to the computation of the potential flow through ducts.

The application of a boundary integral or "panel" method to duct flows is described. The method is capable of computing the three dimensional, steady state, subsonic, linearized (Prandtl-Glauert) potential flow about general configurations. The method is characterized by the application of a Dirichlet boundary condition and of "compressible"...

ARSPNSC: A method to calculate subsonic steady and unsteady potential flow about complex configurations

A new method ARSPSC is described for the calculation of steady and time-linearized unsteady subsonic potential flow about complex 2-D and 3-D configurations. The method belongs to the category of the so-called panel methods. Applications have been made to a 2-D oscillating flat plate, a 2-D multi-component airfoil with oscillating flap and a 3-D...

A method for computing the three—dimensional flow about wings with leading—edge vortex separation Part II: Description of computer program VORSEP

In part I of this report a method is described for computing the incompressible flow about slender, thin wings with leading-edge vortex separation. It is assumed that both the wing and the flow field are symmetric with respect to the x—z plane. The method can handle delta—like wings of quite general planform and shape. However, in the...

An approximate method for computing inviscid vortex wake roll-up. Part I: Theory and application

In this report an approximate method is described for computing, through the unsteady analogy, the shape of steady vortex wakes downstream of aircraft configurations in steady flight. In the analogy the steady fully three-dimensional problem is reduced to a two-dimensional timedependent problem, corresponding to the evolution of a two...

A multigrid algorithm for steady transonic potential flows around aerofoils using Newton iteration

The application of multigrid relaxation to transonic potential-flow calculation was investigated. Fully conservative potential flows around aerofoils were taken as test problems. The solution algorithm was based on Newton iteration. In each Newton iteration step, multigrid relaxation was used to calculate correction potentials. It was found that...

Aspects of second- and third-order panel methods demonstrated for the two-dimensional flat plate problem

Characteristics of three second-order and two third-order panel method formulations for the incompressible flow about a flat plate at incidence are investigated. The second order methods employ quadratic representations for the doublet distribution, either based on quadratic B-splines or on a combination of a Taylor series expansion and finite...

A calculation method of the viscous flow around multi-component airfoils

The viscous flow around multi-component airfoils has been calculated by solving incompressible potential flow and boxindary layer problems iteratively. The potential flow problem is solved by a revised version of the 2D NLR panel method. A model transport equation of turbulent stress is employed to calculate the turbulent boundary layer. The...

Modified version of LTRAN2; a calculation method for inviscid transonic flow about thin airfoils in moderately slow unsteady motion

A method is discussed for the calculation of inviscid transonic flow about thin airfoils in moderately slow unsteady motion. It is an extension of a method which was developed by Ballhaus and Goorjian of NASA Ames and which is applicable for strictly slow unsteady motions only. The modifications involve extra unsteady terms in the boundary...

Application of the NLR Panel Method to a swept-wing/body combination with part-span flaps at low speed and comparison with experimental results

With the purpose of evaluating the adequacy of the NLR Panel Method with respect to the prediction of the flow around 3-D configurations with mechanical high-lift devices, potential flow calculations have been carried out for a swept-wing/body combination with part-span flaps at low speed. Several configurations as well as several calculation...