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研究了当气流偏离喷管超音速段对称轴时，所引起的锥型喷管的推力偏心．用特征面参数化方法数值模拟了喷管的非对称流场，得到了锥型喷管在不同扩张角和采用不同的初值面时，喷管侧向推力分量沿轴向的变化，及其零点位置在轴线上的分布规律，对微推偏喷管的设计具有参考价值．所得结果与现有的实验数据的吻合程度是令人满意的
The thrust eccentricity of the conical nozzle was studied when the airflow deviated from the symmetrical axis of supersonic nozzle. The numerical simulation of nozzle asymmetric flow field is carried out by the parameterized method of characteristic surface. The variation of lateral thrust component of nozzle in the axial direction under different expansion angles and different initial values is obtained, The distribution of zero position on the axis is of reference value to the design of micro push-off nozzle. The obtained results are in good agreement with the existing experimental data