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- W2334806904 abstract "A Nonlinear-Indicial-Response (NIR) based aerodynamic model was applied to a tailless aircraft configuration whose delta-like planform had a leadingedge sweep of 65°. This new application of the aerodynamic model was incorporated into a full aircraft simulation. For the first phase of this application, the aerodynamic modeling was restricted to the rolling moment coefficient for body-axis rolling maneuvers at high angles of attack. This aerodynamic modeling is capable of handling multiple time scales, the longer of which are associated with the relatively slow response of vortex breakdown to the changes in the orientation of the maneuvering aircraft. Incorporation of an aerodynamic model that accounted for these time scales in the simulation significantly degraded the performance of a control law based on conventional aerodynamic models. This control law previously produced acceptable first-order response to body-axis roll rate commands at high angles of attack. This degradation shows that not allowing for time lags in the aerodynamic response can lead to inaccurate simulations, and thus lead to sub-optimal control laws." @default.
- W2334806904 created "2016-06-24" @default.
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- W2334806904 date "1997-08-11" @default.
- W2334806904 modified "2023-09-27" @default.
- W2334806904 title "Application of a Nonlinear-Indicial-Response model to a tailless aircraft simulation" @default.
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- W2334806904 doi "https://doi.org/10.2514/6.1997-3644" @default.
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