NACA66-314 a=0.5
NACA66314a=0.5
Curve fits of basic Javafoil data for NACA66-314 a=0.5, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -1.856e-04*α
3 + 7.408e-04*α
2 + 1.151e-01*α + 2.339e-01
Drag: Cd = f(α) = 1.245e-06*α
3 + 4.347e-04*α
2 + -1.751e-03*α + 7.835e-03
Moment: Cm = f(α) = 1.265e-05*α
3 + 1.116e-04*α
2 + -3.380e-03*α + -4.130e-02
Lift: Cl = f(α) = -2.365e-04*α
3 + 3.571e-04*α
2 + 1.185e-01*α + 2.388e-01
Drag: Cd = f(α) = -8.879e-06*α
3 + 3.444e-04*α
2 + -9.867e-04*α + 6.024e-03
Moment: Cm = f(α) = 4.223e-06*α
3 + 5.399e-05*α
2 + -2.796e-03*α + -4.147e-02
Lift: Cl = f(α) = -2.336e-04*α
3 + -3.287e-04*α
2 + 1.244e-01*α + 2.413e-01
Drag: Cd = f(α) = 5.309e-07*α
3 + 8.727e-05*α
2 + 1.343e-04*α + 5.753e-03
Moment: Cm = f(α) = 1.013e-06*α
3 + 7.111e-06*α
2 + -2.063e-03*α + -4.238e-02
Lift: Cl = f(α) = -2.467e-04*α
3 + -2.870e-04*α
2 + 1.255e-01*α + 2.409e-01
Drag: Cd = f(α) = 2.529e-07*α
3 + 7.295e-05*α
2 + 1.338e-04*α + 5.365e-03
Moment: Cm = f(α) = 7.833e-07*α
3 + 6.217e-06*α
2 + -2.057e-03*α + -4.238e-02