Abstract
This paper presents a method for the computation of the static and dynamic stability derivatives of generic airfoils using high fidelity Computational Fluid Dynamics. Aerodynamic coefficients are calculated for NACA 0012 airfoil and flat plate at different angles of attack. Results of lift coefficient are validated with experimental data. Static and dynamic stability derivatives are calculated by oscillating the airfoil geometry at suitable frequency. Simulations are performed at various flight conditions in terms of angles of attack, frequencies and oscillation amplitudes. The aim of the work is to decipher the behaviour of longitudinal damping derivatives used in flight mechanics through CFD. This approach enables the efficient and accurate computation of dynamic derivatives. Calculations are done for constant air velocity altering only the angle of attack. Inviscid model is tested since its results nearly match with experimental data. The simulations show that the nonlinear characteristics of the stability derivatives are captured by varying angle of attack.
Highlights
Design cycle of modern aircraft has reduced significantly during recent years, partly due to introduction of computers on various stages of design
Complexity in the design of manned and unmanned vehicles is gradually introduced for improved manoeuvrability and versatile mission requirements, which increases the requirement for precise guess of aerodynamic coefficients and dynamic stability derivatives during the preliminary design stage
In nonlinear system [12,13,14,15] importance of dynamic derivatives has increased due to flight manoeuvres by UAVs and other flight vehicles. in recent times, Computational Fluid Dynamics (CFD) is used as an another tool to guess aerodynamic stability derivatives
Summary
Design cycle of modern aircraft has reduced significantly during recent years, partly due to introduction of computers on various stages of design. In 1911 concept of these dynamic derivatives was given by Byran[1].Different mathematical models use these dynamic derivatives to calculate moments and aerodynamic forces of aircrafts. For static stability derivatives wind tunnel test give good estimation but due to complex test-setup, fast design modification and time to perform these experiment, other methods such as DATCOM [10], and ESDU [11] are used. These two methods are fast compared to wind tunnel. In recent times, Computational Fluid Dynamics (CFD) is used as an another tool to guess aerodynamic stability derivatives. These derivatives are calculated for flat plate
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