Effect of Cold Jet Plume on Aerodynamics Coefficients

Abstract

Experiments are carried out on a blunt-cone-cylinder-flare geometry to study the effect of Mach 2.65 jet plume interaction with Mach 5 freestream on overall aerodynamic coefficients. Supersonic jet plume pressure ratios of 0 to 158 are simulated, and the angle of attack is varied from to . Flow features are captured through Schlieren and oil flow visualization. The isolation of load measuring and load nonmeasuring parts and elimination of jet reaction force are confirmed through tests. Under jet-off conditions, with an increase in the angle of attack, the flow separation on the leeward side moves toward the nose, whereas, on the windward side, the separation moves toward the base. Similar behavior is seen under jet-on conditions. However, due to jet-plume–freestream interaction, separation is more pronounced on the leeward side. In general, as increases, the aerodynamic coefficients decrease irrespective of angles of attack. At the maximum of 158, , , and are decreased by 15, 22, and 30%, respectively. Also moves toward the nose by , , and for , 2, and 4 deg, respectively.