In asymmetric blowing of a gas into the supersonic part of a nozzle the main flow is perturbed by the jet which is being blown. Two interaction regimes are distinguished.In the first the perturbation of the main flow does not extend to the side of the nozzle opposite to the blast: the central angle subtended by the perturbation of the exit section of the nozzle is 2y a < 180 ~ (Fig. i). This regime is characterized by the fact that the curvature of the nozzle has no effect on the magnitude of the lateral force.In the second regime the zone of the perturbed flow extends to the side of the nozzle opposite to the blast (2Ya > 180~and this leads to a decrease in the gradient of the lateral force with respect to the fldw rate of the gas which is being blown. The first regime has been studied in the most detail.The experimental data of [i] indicate the slight influence of the shape and the number of openings in the injection unit through which the blowing is taking place, and also of the distance between them, on the magnitude of the amplification factor X, which is tha ratio of the total lateral force F to the thrust F v of the secondary jet in the vacuum in the case of axisymmetric blowing of gas into a Laval nozzle.In [2] a study was made of the effect on the amplification factor of the location of the injector along the length of the supersonic part of the nozzle when a secondary gas is being blown through single cylindrical openings of different diameter d.Experimental data on the amplification factor were generalized into a single curve ([2], Fig. I) in dimensionless coordinates K ~ = K/Ka, Ll/d (K is the current value of the amplification factor, K a is the value of the amplification factor when gas is blown through axL opening located in the immediate vicinit[ of the eXito section).These data were obtained with combinations of the parameters G 2, a, and L 1 which guarantee that the condition 2"y a < 180 ~ O is fulfilled.IIere G 2 = G2/G 1 is the relative mass flow rate of the gas which is being blown, G 1 is the flow rate through the main nozzle, a is the angle between the axis of the blowing O channel and the axis of the main nozzle, L 1 ~ LI/L is the relative distance between the blowing section and the exit section of the nozzle, and L is the length of the supersonic part of the nozzle.The flow in a nozzle with gas being blown and with a perturbation extending to the side of the nozzle opposite to the blowing (2y a > 180 ~ ) has a number of peculiarities which determine the specific effecton the amplification factor of the way in which the blowing openings are distributed along the length of the nozzle and in the injection unit.In the present study, which is a continuation of [2], the amplification factor was experimentally determined in the case of a transverse gas jet being blown into the supersonic parts of axisymmetric nozzles with various dispositions of the openings alon~ the length of the nozzle and in the injection unit during processes characterized by the extension of the perturbation to the side ...