A preliminary investigation into Euler methods for application to multielement aerofoils for high lift
Abstract
The full potential equation is solved for flow past a circular cylinder and the results obtained are compared with the benchmark solution of Rayleigh and Janzen. Euler's equations of motion are derived in a Cartesian coordinate system. A general form of the equations for orthogonal curvilinear coordinate systems is also given. The equations in Cartesian coordinates are discretized. The main methods are those or Lax, MacCormack, and Hall. The first order finite difference technique and first and second order cellvertex integral method are applied to the problem of a 10 percent symmetric thin airfoil in subsonic freestream. The results are compared to those or the linearized model. A flow solution over a circular cylinder is treated. The Euler equations are developed in inverted cylindrical polar coordinates. The inverse conformal mapping is used to map the exterior region of the circle onto the internal region. A subsonic freestream flow is considered for a leading quarter of the circle using the second order finite difference technique and the second order cellvertex method. Results are compared with those obtained using the fullpotential model. For a halfcircle, results for a slightly supercritical freestream are given.
 Publication:

Ph.D. Thesis
 Pub Date:
 November 1987
 Bibcode:
 1987PhDT........66B
 Keywords:

 Airfoils;
 Circular Cylinders;
 Computational Fluid Dynamics;
 Euler Equations Of Motion;
 Lift;
 Cartesian Coordinates;
 Cylindrical Coordinates;
 Finite Difference Theory;
 Polar Coordinates;
 Fluid Mechanics and Heat Transfer