Abstract
ABSTRACT The stability analysis of an aircraft configuration is studied using a new system stability method called the weight function method. This new method finds a number of weight functions that are equal to the number of firstorder differential equations. This method is applied for longitudinal and lateral motions on a delta-wing aircraft, the X-31, designed to break the stall barrier. Aerodynamic coefficients and stability derivatives obtained using the Digital DATCOM code have been validated with the experimental Low-Speed Wind tunnel data obtained using the German–Dutch Wind Tunnel (DNW–NWB). Root Locus Method is used to validate the method proposed in this paper.
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