Vortical flow analysis for F-106B configuration

Abstract

The three-dimensional Euler aerodynamic method is applied to basic F-106B wing-fuselage geometries over an angle-of-attack range in the subsonic and transonic speeds to examine vortical flow behavior. The use of this method to provide meaningful vortex breakdown information is explored. This Euler solution algorithm uses a C-H mesh with 80625 grid points to represent the flowfield. Contours of axial velocity and total pressure, spanwise surface pressure and velocity vectors at cross flow planes, together with contours of suction pressure and total pressure on the leeward surface of the wing, were used to examine the vortex breakdown details.