The Fin Can Assembly includes the fins, fin can, and a thermal barrier layer between the motor casing and fin can.
- The Assembly shall be designed in such a way that the static stability of the rocket remains greater than or equal to 2.0 calibers throughout the entire flight.
- The Assembly shall withstand thermal heating due to streamline stagnation and skin friction.
- The Assembly shall withstand lifting loads proportional to dynamic pressure and fin area.
Stagnation Temperature
The stagnation temperature on the root side of the leading edge of the fins is given by:
formulize T_stag = T_static + 1/(2*c_p) * (v_2 - v_1)^2
where v_2 - v_1 = v_2 * cos(Lambda)
where c_p = 1004.5 for air and Lambda is the sweep angle of the fins
Dynamic Pressure