Acceleration due to aerodynamic forces
[acc] = CL_fo_aeroAcc(v, rho, coef_aero)
Computes the acceleration due to aerodynamic forces.
The acceleration is obtained by:
acc = 1/2 * rho * v^2 * coef_aero
with:
coef_aero = aero_vec * area / mass
aero_vec is the aerodynamic coefficients vector with coordinates in the frame in which acc components are to be computed. It is parallel to the aerodynamic force and points to the same direction.
aero_vec can be computed for a flat plate by CL_mod_aeroPanelCoefV.
Notes:
- The velocity (v) is the module of the velocity vector (velocity relative to the atmosphere).
- The coordinates frame can be any frame. The origin of the frame does not matter.
Norm of velocity vector (velocity relative to the atmosphere) [m/s]. (1xN or 1x1)
Density of the atmosphere [kg/m^3]. (1xN or 1x1)
Aerodynamic coefficients vector * area / mass [m^2/kg]. (3xN or 3x1)
Acceleration vector [m/s^2]. (3xN)
CNES - DCT/SB