External Aerodynamics Simulations in a Rotating Frame of Reference

Table 2

Comparison of stability derivatives for the NACA 0012 at α = 0° and Mach = 0.2.

Derivatives	UNS3D	Limache and Cliff [6]
𝐶𝑙𝑞	−5.225	−5.250
𝐶𝑚𝑞	−1.932	−1.766