In view of the computational restrictions imposed upon any implementable flight control algorithm, a linear model reference adaptive controller which does not require the explicit online identification of aircraft parameters has been developed. Related analysis shows this algorithm to be at least stable in the sense of bounded plant-model errors provided that certain constraints can be satisfied. If in addition the open loop system satisfies the conditions of perfect model following the closed loop system will be asymptotically stable. Procedures were developed for satisfying the constraints and for adjusting the transient and steady state behavior. Results using the linearized lateral F-8 equations show the algorithm to be capable of adjusting to sudden flight condition changes within 1-2 seconds.