<Li> t is the airfoil thickness at a given section, and </Li> <Li> c is the chord length at a given section . </Li> <Li> K (\ displaystyle K) is a factor established through CFD analysis: </Li> <P> K = 0.87 for conventional airfoils (6 series) K = 0.95 for supercritical airfoils </P>

What are some of the effects of reaching force divergence mach number