The efficiency of gas dynamic thrust vector control for advanced space planes was investigated in the form of a parametric study. Geometry, bleeding mass flows and pressure ratios were varied to obtain a survey on the performance of such control systems. Fully active control of nozzle flow along the whole ramp requires excessively high secondary mass flows which are not available in space plane application and furthermore, which suppress the advantageous selffocusing effect. Fully passive control is insufficient to balance the wall pressure especially under strong overexpanded conditions. Finally, a combination of active and passive control or active control in selected areas allows for control of nozzle flow with reduced mass flows. With respect to the diversion of the forebody boundary layer, one of the required two chambers must be positioned in the region of the overexpanded nozzle flow in order to obtain a high suction capacity. The experimental results show that only the forebody boundary layer with maximum mass flows between 3 % and 5 % or flow derived from the external flow in the afterbody region (short side walls) should be used for the wall bleeding normal to flow direction. Mass flows separated from the high energy jet used for bleeding normal to main flow direction should be as small as possible in order to reduce the impulse losses in the propelling direction Therefore, this control system can be realized with a secondary jet at the lower side of the afterbody which presses the primary jet to the ramp so that the impuls vector remains in the propelling direction. Due to a number of parameters which are necessary for the description of the afterbody flow field, an attempt was made to develop a semiempirical method for a novel design and optimization of the bleeding system with the help of several characteristic parameters such as pressure ratios which can be obtained from the investigation of individual problems.