EPPLER 668
EPPLER 668 AIRFOIL
New! Bulk download of polars in Excel format:
e668.xlsx Curve fits of basic Javafoil data for EPPLER 668, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -3.135e-04*α
3 + -3.443e-04*α
2 + 1.282e-01*α + 6.634e-01
Drag: Cd = f(α) = -8.318e-06*α
3 + 3.992e-04*α
2 + -1.217e-03*α + 4.204e-03
Moment: Cm = f(α) = 1.577e-05*α
3 + 4.521e-04*α
2 + -5.942e-03*α + -1.356e-01
Lift: Cl = f(α) = -3.183e-04*α
3 + -2.968e-04*α
2 + 1.294e-01*α + 6.613e-01
Drag: Cd = f(α) = -1.742e-05*α
3 + 3.629e-04*α
2 + -2.834e-05*α + 1.668e-03
Moment: Cm = f(α) = -9.493e-06*α
3 + 3.620e-04*α
2 + -3.174e-03*α + -1.388e-01
Lift: Cl = f(α) = -2.394e-04*α
3 + -4.161e-04*α
2 + 1.275e-01*α + 6.621e-01
Drag: Cd = f(α) = 6.513e-06*α
3 + 1.252e-04*α
2 + -1.465e-04*α + 3.819e-03
Moment: Cm = f(α) = -2.407e-06*α
3 + 3.704e-05*α
2 + -1.660e-03*α + -1.362e-01
Lift: Cl = f(α) = -2.646e-04*α
3 + -3.651e-04*α
2 + 1.289e-01*α + 6.607e-01
Drag: Cd = f(α) = -1.486e-06*α
3 + 7.041e-05*α
2 + 2.072e-04*α + 4.723e-03
Moment: Cm = f(α) = -3.456e-06*α
3 + 2.969e-05*α
2 + -1.595e-03*α + -1.361e-01