The flow characteristic and starting method of two-dimensional divergent dual throat nozzle were studied numerically. The results show that there will be normal shock waves in the divergent zone of the dual throat nozzle, which result in great loss in total pressure and choke at the second throat, thus the nozzle can not start. In the condition of low nozzle pressure ratio, a large separation region, which weakens the shock waves, can be formed by injection in the throat, and the nozzle can start; in the condition of high nozzle pressure ratio, a large separation region will not be formed. A large separation region in the nozzle can be generated by injecting in the divergent, thus the oblique shock is formed instead of the normal shock, the total pressure loss decreases, and the nozzle can start.
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̷�ۿ�,����.��Ԫ˫�����������ʸ����ܵ���ֵģ���о�[J].���ն���ѧ��,2007,22 (10): 1678-1684 Tan Huijun,Chen Zhi.A computational study of 2-D dual throat fluidic thrust vectoring nozzles[J].Journal of Aerospace Power,2007,22 (10): 1678-1684 (in Chinese)
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