NACA66-515 a=0.8
NACA66515a=0.8
Curve fits of basic Javafoil data for NACA66-515 a=0.8, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -1.910e-04*α
3 + -9.244e-05*α
2 + 1.187e-01*α + 4.833e-01
Drag: Cd = f(α) = -1.504e-07*α
3 + 4.087e-04*α
2 + -1.493e-03*α + 8.080e-03
Moment: Cm = f(α) = 2.277e-05*α
3 + 2.801e-04*α
2 + -5.655e-03*α + -9.826e-02
Lift: Cl = f(α) = -2.194e-04*α
3 + -3.430e-04*α
2 + 1.208e-01*α + 4.891e-01
Drag: Cd = f(α) = -7.708e-06*α
3 + 3.382e-04*α
2 + -7.949e-04*α + 5.947e-03
Moment: Cm = f(α) = 7.290e-06*α
3 + 1.815e-04*α
2 + -4.246e-03*α + -9.977e-02
Lift: Cl = f(α) = -2.615e-04*α
3 + -5.270e-04*α
2 + 1.273e-01*α + 4.858e-01
Drag: Cd = f(α) = -2.386e-05*α
3 + 2.365e-04*α
2 + 1.615e-03*α + 1.941e-03
Moment: Cm = f(α) = -9.901e-06*α
3 + 9.807e-05*α
2 + -1.643e-03*α + -1.030e-01
Lift: Cl = f(α) = -2.142e-04*α
3 + -8.148e-04*α
2 + 1.252e-01*α + 4.933e-01
Drag: Cd = f(α) = -1.102e-07*α
3 + 8.127e-05*α
2 + 3.283e-04*α + 5.233e-03
Moment: Cm = f(α) = -9.065e-07*α
3 + 2.561e-05*α
2 + -2.003e-03*α + -1.015e-01