NACA64-214 a=0.6
NACA64214a=0.6
Curve fits of basic Javafoil data for NACA64-214 a=0.6, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -2.369e-04*α
3 + 3.402e-04*α
2 + 1.218e-01*α + 1.617e-01
Drag: Cd = f(α) = -1.584e-05*α
3 + 3.305e-04*α
2 + 5.513e-05*α + 4.924e-03
Moment: Cm = f(α) = 8.298e-07*α
3 + 4.392e-05*α
2 + -1.462e-03*α + -3.047e-02
Lift: Cl = f(α) = -2.216e-04*α
3 + -2.539e-04*α
2 + 1.251e-01*α + 1.687e-01
Drag: Cd = f(α) = 7.460e-07*α
3 + 1.134e-04*α
2 + 7.101e-05*α + 6.509e-03
Moment: Cm = f(α) = 3.324e-07*α
3 + 1.188e-05*α
2 + -1.199e-03*α + -3.026e-02
Lift: Cl = f(α) = -2.233e-04*α
3 + -2.154e-04*α
2 + 1.260e-01*α + 1.685e-01
Drag: Cd = f(α) = -5.426e-08*α
3 + 8.946e-05*α
2 + 1.059e-04*α + 5.454e-03
Moment: Cm = f(α) = 4.058e-07*α
3 + 8.800e-06*α
2 + -1.222e-03*α + -3.030e-02
Lift: Cl = f(α) = -2.197e-04*α
3 + -2.157e-04*α
2 + 1.263e-01*α + 1.693e-01
Drag: Cd = f(α) = -1.358e-08*α
3 + 7.293e-05*α
2 + 1.003e-04*α + 5.229e-03
Moment: Cm = f(α) = 6.041e-07*α
3 + 6.458e-06*α
2 + -1.247e-03*α + -3.032e-02