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.
