Abstract:
The dynamic pitch derivatives of an axisymmetric conceptual projectile were examined
using Computational Fluid Dynamics (CFD). Stability coefficients and derivatives are
used to determine a vehicle’s motion and are critical for the design of flight vehicles
and control. Using CFD to estimate the flight parameters of new munition designs
has the potential to significantly improve performance and reduce research and testing
costs that are required for wind tunnel testing. In this research a methodology of
CFD analysis is established through validation of two test cases and then applied on
a new conceptual design. The static cases were also implemented in missile DATCOM
for a comparative analysis. The dynamic damping derivatives were calculated using
the forced oscillation approach. For the validation of the CFD method “Basic Finner
model” was used. The pitch damping coefficients were simulated for angles of attack
from 0o to 20o and a good agreement was found between the CFD and experimental
results. A conceptual geometry was also designed and simulated at a Mach number
of 1.5. A parametric analysis was also conducted for the variation of Mach number
and reduced pitch rate on pitch damping coefficients for the new design. Through this
study the use of CFD as a tool for determining fast and consistent estimates for the
Aerodynamic stability parameters was established.
