NACA63-413
NACA 63-413
Curve fits of basic Javafoil data for NACA63-413, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -2.418e-04*α
3 + -4.340e-04*α
2 + 1.213e-01*α + 4.294e-01
Drag: Cd = f(α) = -1.329e-05*α
3 + 3.451e-04*α
2 + -1.225e-04*α + 5.099e-03
Moment: Cm = f(α) = 6.287e-07*α
3 + 2.002e-04*α
2 + -2.158e-03*α + -8.860e-02
Lift: Cl = f(α) = -2.696e-04*α
3 + -5.426e-04*α
2 + 1.256e-01*α + 4.265e-01
Drag: Cd = f(α) = -2.581e-05*α
3 + 2.493e-04*α
2 + 1.484e-03*α + 3.406e-03
Moment: Cm = f(α) = -1.129e-05*α
3 + 1.183e-04*α
2 + -5.803e-04*α + -8.913e-02
Lift: Cl = f(α) = -2.324e-04*α
3 + -7.882e-04*α
2 + 1.249e-01*α + 4.317e-01
Drag: Cd = f(α) = -1.604e-06*α
3 + 9.454e-05*α
2 + 3.190e-04*α + 5.439e-03
Moment: Cm = f(α) = -1.033e-06*α
3 + 3.575e-05*α
2 + -9.274e-04*α + -8.765e-02
Lift: Cl = f(α) = -2.276e-04*α
3 + -7.701e-04*α
2 + 1.250e-01*α + 4.310e-01
Drag: Cd = f(α) = -2.252e-06*α
3 + 7.462e-05*α
2 + 3.596e-04*α + 5.397e-03
Moment: Cm = f(α) = -1.398e-06*α
3 + 2.627e-05*α
2 + -8.908e-04*α + -8.752e-02