Effect of wing strake arrangement on flight stability characteristics of a generic aircraft

Abstract

The successful estimation of stability characteristics in response to changes in aircraft’s flight conditions is the primary goal of flight stability. With the help of Computational Fluid Dynamics, an assessment of the longitudinal stability characteristics is performed. Examination of flight stability characteristics is developed with the assistance of the SAACON UCAV validation study. A comparative analysis in conjunction with experimental static results of JF-17 thunder aircraft finalized the validation process. The study has analyzed the longitudinal static and dynamic aerodynamic lift, drag and moment coefficients, and the aerodynamic center and center of pressure location estimation to understand the effect of wing-strake. With the help of forced oscillations, the aircraft’s dynamic behavior is estimated for a moment and lift through dynamic damping coefficients. Also, a comparative study on the Prototype-03 and Prototype-04 of JF-17 Thunder aircraft has been performed to understand the impact of wing-strake arrangement on aircraft flight stability under various flight conditions. Conclusively, due to the addition of wing-strake, the flight stability of the aircraft decreases.