Stability Derivative Estimation: Methods and Practical Considerations for Conventional Transonic Aircraft

摘要

An assessment of various stability derivative prediction methods is presented and comparisons are made to flight derived static and dynamic stability derivatives for a transonic business jet and the Douglas D558-Ⅱ research aircraft. Prediction methods include the forced oscillation method using FUN3D, the vortex lattice code AVL, and handbook methods. Flight-based stability derivatives were extracted through analysis of aircraft response to control surface doublets. A second component of this paper discusses the accuracy requirements for stability and control derivatives, their effect on the basic aircraft lateral/directional and longitudinal modes, and subsequent impact on aircraft design.