Finite difference calculation of incompressible flow through a straight channel of varying rectangular cross section, with application to low speed wind tunnels

A fully-conservative- finite difference algorithm is described to calculate the incompressible flow through a straight channel of varying rectangular cross section. Both the width and the height of the channel may vary independently. The algorithm has been used successfully in the design of the German-Dutch low speed wind tionel (DNW).

The design and aerodynamic characteristics of an 18% thick shock-free airfoil (NLR 7501)

The design and experimental verification of a thick (18 %), shock free airfoil is described. The design was performed, using the NLR hodograph theory for transonic airfoil design. The airfoil was experimentally investigated in the NLR Pilot tunnel.

The calculation of aerodynamic characteristics of wing-body combinations at subsonic flight speeds

Surface panel methods and finite difference methods are reviewed with respect to the use in the design of aeroplanes. It is concluded that there is a need for inverse surface panel type methods to diminish the trial and error character of the design process. Finite difference methods based on transonic small perturbation theory have to be based...