The jet thrust and the required throat area for a propulsion nozzle may be calculated from the measured stagnation pressure, the stagnation temperature, and the upstream static pressure of the flow entering the nozzle. For flows with nonuniformities in the stagnation quantities and in exit static pressure, integral relations are developed which allow the calculation of increments to thrust and throat area due to the nonuniformities. To illustrate the important nonuniformity interactions, the integral relations are linearized for the special case of uniform 7. As a result, one finds expressions for the correction factors to thrust and area which are the sum of terms that consist of nonuniformity parameters multiplied by sensitivity or influence coefficients. The magnitude of these influence coefficients depends on nozzle parameters and show the relative importance of various kinds of nonuniformities.