Thrust vector control (TVC) techniques for plug nozzles, such as canting and displacing the central plug, e uid injection, differential throttling, and use of e aps, are reviewed. Some methods, such as displacing the central plug, may only be of academic interest or useful for small motors. Although emphasis is on annular plug nozzles, reference is made to linear plug nozzles. The analyses are based on limited experimental data and engineering calculations. The results are intended for a e rst assessment and ranking of TVC methods for plug nozzles. They are based on a reference annular plug nozzle rocket engine with a thrust in the order of 1 MN and a launcher diameter of about 5 m, as may be found on modern launchers, e.g., the Ariane 5 cryogenic e rst stage. When a particular TVC method is used, the effectiveness may depend on the longitudinal position of the center of mass of the launcher. Therefore, either the TVC is given in terms of the thrust dee ection angle or in terms of the moment that may be generated. Only if e aps are used, it is possible to generate roll moments with a single annular plug nozzle. Nomenclature a = velocity of sound c = coefe cient F = thrust I = impulse i = local inclination of the plug surface l = distance M = Mach number Mo = moment m = mass e ow rate over e ap Q = mass e ow rate main e ow q = mass e ow rate e uid injection R = radius r = (inner) radius T = torque V = velocity a = plug inclination angle b = shock angle c = ratio of specie c heats d = thrust vector angle h = position angle, e ap angle u = e ap rotation angle Subscripts c = combustion chamber e = exit conditions f = thrust lat = lateral max = maximum sp = speciec t = throat 1 = incoming e ow 2 = e ow behind shock