An integrated dynamic model of a two-variable (normal shock position and engine speed) inlet-engine combination is formulated on the basis of the idea in author’s former paper

but the effect of engine flow feedback on the inlet during transient period is taken into consideration and the matrix fraction description method is applied to transforming frequency domain into state space domain in the model. The results of a sample digital simulation for NASA 48cm inlet-J85 engine combination show that the method of formulation is satisfactory.