EPPLER 1230
EPPLER 1230 AIRFOIL
New! Bulk download of polars in Excel format:
e1230.xlsx Curve fits of basic Javafoil data for EPPLER 1230, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -1.878e-04*α
3 + 4.932e-04*α
2 + 1.286e-01*α + 4.983e-01
Drag: Cd = f(α) = -1.596e-05*α
3 + 3.023e-04*α
2 + 6.240e-04*α + 3.726e-03
Moment: Cm = f(α) = -4.188e-06*α
3 + 1.081e-04*α
2 + -1.228e-03*α + -7.933e-02
Lift: Cl = f(α) = -1.878e-04*α
3 + 5.406e-04*α
2 + 1.306e-01*α + 4.941e-01
Drag: Cd = f(α) = -1.819e-05*α
3 + 2.375e-04*α
2 + 1.367e-03*α + 2.177e-03
Moment: Cm = f(α) = -4.739e-06*α
3 + 7.072e-05*α
2 + -8.547e-04*α + -7.917e-02
Lift: Cl = f(α) = -1.528e-04*α
3 + 3.383e-04*α
2 + 1.286e-01*α + 5.009e-01
Drag: Cd = f(α) = -1.870e-06*α
3 + 8.885e-05*α
2 + 1.941e-04*α + 5.553e-03
Moment: Cm = f(α) = -4.295e-07*α
3 + 2.324e-05*α
2 + -1.118e-03*α + -7.774e-02
Lift: Cl = f(α) = -1.641e-04*α
3 + 2.670e-04*α
2 + 1.298e-01*α + 5.032e-01
Drag: Cd = f(α) = 3.303e-07*α
3 + 9.004e-05*α
2 + 5.016e-05*α + 4.661e-03
Moment: Cm = f(α) = 3.255e-07*α
3 + 2.355e-05*α
2 + -1.165e-03*α + -7.783e-02