A method for developing cascade profiles for high subsonic potential flows to satisfy prescribed inlet and exit flow conditions and approximately prescribed cascade solidity is given. The method is based on the assumption that the compressibility of a gas can be represented by a linear pressure-volume relation (the Karman-Tsien approximation). I t is shown that with the proper selection of this pressure-volume relation, the error in specific volume in the linearized gas as compared to an isentropic gas at the same velocity is less than 2 per cent of the isentropic stagnation specific volume for Mach Numbers between approximately 0.4 to 0.9. An example shows that this Mach Number range covers almost the entire length of the cascade profile for an inlet Mach Number of 0.7 and a deflection of 22°. The deviation of the fluid angle from the blade angle at exit and the influence of inlet Mach Numbers on deviation are found to be in substantial agreement with previous experimental results.