Abstract
This paper presents the results of an investigation for the jet tab effect in the nozzle flow. The three dimensional inviscid flowfield through the nozzle with the tab inserted into the exhaust stream is computed by the finite difference procedure due to LAX. For various blockage area ratio, the lateral and axial forces for the thrust vector control are obtained by integrating the pressures over the nozzle wall and around the tab and the efficiency of tabs (side thrust/loss in axial thrust) is discussed.
The results show that the efficiency of the tab which covers the wall of about 47% in the meridian direction at the nozzle exit is the highest, the side thrust is dependent on the tab width and thickness as well as the blockage ratio and the loss in axial thrust is decreased with the increase of tab width.
