DAI Lylia

Presently, there seem to be a high demand for exact solutions through analytical, experimental-measurement and computational in the field of aerospace engineering. The experimental procedure involving wind tunnel testing leads to high costs due to expensive materials needed for wind tunnel testing and turnaround times necessary to accomplish the experiments. Therefore, numerical methods are nowadays extensively used to evaluate the flow field in and/or over a wedge at supersonic Mach numbers.

Among the more promising design techniques proposed to minimize the drag were concepts incorporating 2-D-wedge nozzles into aircraft. Such nozzles integrate well with tapering, nearly rectangular after body fuselage contours thereby improving thrust-minus-drag performance. Thrust vectoring and reversing, shown to be better suited for incorporation into 2-D nozzles, would further improve the aircraft maneuverability and reduce take-off and landing distances.