Experimental Investigation of the Influence of Transverse Dual protuberances on the Thrust Vector of a Supersonic C-D nozzle

In this study, effects of the use of dual transverse protuberances (DTP) as a new, low cost and simple method in controlling the thrust vector in a C-D  nozzle, whose nominal Mach number is 2, was investigated. The protuberances used are two cylindrical shapes that are placed in front of the flow in the divergence part of  nozzle. Protuberances are installed in 80% of the length of the nozzle divergence section from nozzle throat, transversely and at a 45° angle to each other. The flow field was investigated by schlieren imaging, along with measuring the pressure distributions on the nozzle walls. The results show that using the DTP in the nozzle can increase the angle of the thrust vector to 3.5 degrees in the examined conditions. Also,it can be achived in compare to using a single protobrance with lower thrust loss up to 5.5%.