03.4 - Applied Aerodynamics
NUMERICAL EVALUATION OF DYNAMIC STABILITY DERIVATIVES FOR HIGH LIFT DEVICES
H. Ur Rahman¹, A. Maqsood¹, R. Riaz¹, L. Dala, Northumbria University, United Kingdom; ¹National University of Sciences & Technology, Pakistan
High lift devices (HLD) are wing surfaces that change the aerodynamic characteristics for desirable performance in specific flight regime. HLD improve the slow flight performance and help reducing the stall speed by increasing maximum lift coefficient. Different types of high lift systems are operational in aviation industry. The major push during the design activity is to increase the static aerodynamic performance while keeping the aeroacoustic signatures to the minimum. However, often, stability considerations are reported during the experimentation phase. To compensate for any undesirable phenomena, Stability Augmentation Systems (SAS) are deployed to improve the flight characteristics.rnThis research is aimed at finding the fundamental effects of high lift devices on stability characteristics of TC12 airfoil through Computational Fluid Dynamics. Stability derivatives are calculated for four different configurations that are; clean configuration, only slat deployed configuration, only flap deployed configuration and both slat and flap configuration.rn The static and dynamic coefficients are validated for NACA 0012 by using forced oscillation technique and the results were compared with experimental data. Then the same methodology was applied for calculation of static and dynamic stability derivatives of TC12 airfoil for different high-lift configurations. Simulations were performed at various flight conditions in terms of angles of attack, frequencies and oscillation amplitudes while keeping the air velocity constant. This approach enabled the efficient and accurate computation of stability derivatives. rnCalculations were done for constant air velocity altering only the angle of attack. Subsequently, dynamic estimation at different angles of attack is done with 5, 10 and 15 degree flap deflection angles. Using the same methodology, stability derivatives are calculate