A two-dimensional cascade aeroelastic solver for analyzing a multistage turbomachine has been devel- oped and is reported in this paper. The required unsteady aerodynamic forces are obtained from a Euler solver based on a e ux differencing scheme. The aerodynamic solver is coupled with a typical section structural model to calculate the e utter and forced response characteristics. The aeroelastic equations are integrated in time domain by sequentially solving the structural and aerodynamic equations at each time step. The unsteady aerodynamic forces generated by the front row, a rotor row, are used to calculate the response of the blades in the aft rows. Response of the blades because of forces generated by blade (self) vibration are also included in the analysis. EROELASTIC stability (e utter) and forced response be- cause of distortions upstream of the e ow are two of the important considerations in the safe design of turbomachines. For the last several years, NASA Lewis Research Center has been developing aeroelastic analyses for turbomachines. An overview of this research was presented in Ref. 1. The over- view indicated that many analysis methods exist for unstalled e utter and forced response calculations. A range of aerody- namic and structural models have been used to obtain the aeroelastic equations. Both time and frequency domain meth- ods have been used to solve the aeroelastic equations. How- ever, the solution methods and their application were limited to analyzing an isolated blade row. Such an analysis is valid when the rows of blades of a turbomachine are far enough apart so that aerodynamic interaction effects can be neglected. The desire to minimize engine length, however, requires that the blade rows in turbomachines be closely spaced. Reducing the axial gap between the rows makes the aerodynamic inter- action effects, namely, potential e ow interaction and viscous wake interaction, even more important. The potential e ow over a row of airfoils can cause unsteadiness in both the upstream and downstream rows, and the gradients decay with a length scale equal to the pitch or chord of the cascade. The viscous wake, on the other hand, is convected downstream, and its far- e eld rate of decay is much more gradual than that of the po- tential e ow. Its effects may be felt several chords downstream. Thus, wake interaction will be present even when adjacent rows are spaced far apart. Under most conditions, both mech- anisms are present simultaneously. Additional unsteady forces are introduced when the blades in each row are vibrating. Two approaches are followed to analyze rotor› stator inter-