Dynamic stability testing of aircraft—needs versus capabilities

Abstract This paper presents highlights of a recent survey of the future needs for dynamic stability information for such aerospace vehicles as the space shuttle and advanced high-performance military aircraft. The importance of obtaining this information for high-angle-of-attack high-Reynolds-number flight conditions is indicated. A review of the wind-tunnel capabilities in North America for measuring dynamic stability derivatives reveals an almost total lack of such capabilities for Mach numbers above 0.1 at angles of attack higher than 25°. In addition, capabilities to determine certain new cross-coupling derivatives and to obtain information on effects of the coning motion are almost completely lacking. Recommendations are made regarding equipment that should be constructed to remedy this situation. A description is given of some of the more advanced existing facilities, which can be used to satisfy at least partly the immediate needs.

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