Stability and Control Problems of Supersonic Aircraft: Reprinted from Part 3 (July 1 to September 30, 1956) of the Quarterly Bulletin of the National Aeronautical Establishment, Ottawa, Canada

Abstract

IN the past, the required amount of directional stability was dictated mainly by asymmetric power considerations and by the maximum angles of sideslip in manoeuvres permissible from the structural strength viewpoint. The requirement for satisfactory recovery from steady spin would in certain cases influence both the directional stability and control power in such a fashion as ultimately to be the determining factor. Present indications are that the choice of the required degree of directional stability will be based on supersonic lateral dynamic stability considerations, in particular the stability of the so‐called Dutch roll oscillation, or on considerations of avoiding inertia coupling between the lateral and longitudinal degrees of freedom during rolling. Both of these problems will be discussed in some detail later. It should be emphasized, however, that large values of subsonic directional stability will be required for supersonic aircraft in order to provide satisfactory dynamic characteristics at supersonic speeds at high altitudes.

Citation

Michaelson, O.E. (1957), "Stability and Control Problems of Supersonic Aircraft: Reprinted from Part 3 (July 1 to September 30, 1956) of the Quarterly Bulletin of the National Aeronautical Establishment, Ottawa, Canada", Aircraft Engineering and Aerospace Technology, Vol. 29 No. 9, pp. 275-281. https://doi.org/10.1108/eb032870