EPPLER 169
E169 (14.4%)
New! Bulk download of polars in Excel format:
e169.xlsx Curve fits of basic Javafoil data for EPPLER 169, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -2.251e-04*α
3 + -3.760e-07*α
2 + 1.277e-01*α + 4.086e-05
Drag: Cd = f(α) = 5.293e-14*α
3 + 2.023e-04*α
2 + -2.181e-12*α + 4.301e-03
Moment: Cm = f(α) = 6.545e-07*α
3 + 8.638e-15*α
2 + -6.494e-04*α + -4.561e-13
Lift: Cl = f(α) = -2.162e-04*α
3 + -6.692e-07*α
2 + 1.280e-01*α + 7.688e-05
Drag: Cd = f(α) = 2.646e-14*α
3 + 1.607e-04*α
2 + -2.194e-12*α + 4.008e-03
Moment: Cm = f(α) = 5.593e-07*α
3 + 6.459e-14*α
2 + -6.468e-04*α + -4.534e-13
Lift: Cl = f(α) = -1.997e-04*α
3 + -6.692e-07*α
2 + 1.280e-01*α + 7.688e-05
Drag: Cd = f(α) = 2.111e-14*α
3 + 1.057e-04*α
2 + -2.180e-12*α + 4.335e-03
Moment: Cm = f(α) = 5.731e-07*α
3 + 7.993e-15*α
2 + -6.612e-04*α + -4.635e-13
Lift: Cl = f(α) = -1.866e-04*α
3 + -6.692e-07*α
2 + 1.276e-01*α + 7.688e-05
Drag: Cd = f(α) = 3.907e-14*α
3 + 7.941e-05*α
2 + -2.187e-12*α + 4.614e-03
Moment: Cm = f(α) = 5.731e-07*α
3 + 7.993e-15*α
2 + -6.612e-04*α + -4.635e-13