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Static Stability Analysis Based on Conceptual Design

Heping Wang

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Abstract

To estimate the static stability of aircraft in subsonic regime,a numerical calculation model of aerodynamic derivatives is developed based on aircraft geometry parameters from the conceptual design phase.An example for aerodynamic derivatives is given.A comparison of the numerical calculation results to predicted aerodynamic derivatives by a computational fluid dynamics(CFD) method and test data shows that the numerical calculation method based on an aerodynamic configuration generated in the conceptual design phase is rapid and reasonable in operation.

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What this paper is about

To estimate the static stability of aircraft in subsonic regime,a numerical calculation model of aerodynamic derivatives is developed based on aircraft geometry parameters from the conceptual design phase.An example for aerodynamic derivatives is given.A comparison of the numerical calculation results to predicted aerodynamic derivatives by a computational fluid dynamics(CFD) method and test data shows that the numerical calculation method based on an aerodynamic configuration generated in the conceptual design phase is rapid and reasonable in operation.

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Available abstract

To estimate the static stability of aircraft in subsonic regime,a numerical calculation model of aerodynamic derivatives is developed based on aircraft geometry parameters from the conceptual design phase.An example for aerodynamic derivatives is given.A comparison of the numerical calculation results to predicted aerodynamic derivatives by a computational fluid dynamics(CFD) method and test data shows that the numerical calculation method based on an aerodynamic configuration generated in the conceptual design phase is rapid and reasonable in operation.

Key concepts: Aerodynamics, Longitudinal static stability, Computational fluid dynamics, Conceptual design, Stability (learning theory), Stability derivatives, Aerospace engineering, Engineering

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