External Aerodynamics Simulations in a Rotating Frame of Reference

Table 1

Comparison of lift and moment coefficients for the NACA 0012 at α = 0° and Mach = 0.2 at various values of 𝑞 (results from Limache [7] are in parentheses).

𝑞	𝐶𝑙	𝐶𝑚
0.01	−0.051 (−0.053)	−0.02 (−0.018)
0.03	−0.153 (−0.157)	−0.06 (−0.053)
0.05	−0.26 (−0.262)	−0.1 (−0.088)