GOE 300 (FRIEDRICHSHAFEN G20)
GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL
New! Bulk download of polars in Excel format:
goe300.xlsx Curve fits of basic Javafoil data for GOE 300 (FRIEDRICHSHAFEN G20), smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -1.494e-04*α
3 + 5.835e-04*α
2 + 1.167e-01*α + 6.768e-01
Drag: Cd = f(α) = -1.829e-06*α
3 + 2.992e-04*α
2 + -2.008e-03*α + 1.528e-02
Moment: Cm = f(α) = 1.545e-05*α
3 + 6.604e-05*α
2 + -6.423e-03*α + -8.823e-02
Lift: Cl = f(α) = -1.427e-04*α
3 + 6.359e-04*α
2 + 1.164e-01*α + 6.809e-01
Drag: Cd = f(α) = -1.767e-06*α
3 + 2.798e-04*α
2 + -1.972e-03*α + 1.289e-02
Moment: Cm = f(α) = 1.383e-05*α
3 + 7.662e-05*α
2 + -6.116e-03*α + -9.178e-02
Lift: Cl = f(α) = -1.185e-04*α
3 + 8.411e-04*α
2 + 1.146e-01*α + 6.803e-01
Drag: Cd = f(α) = -4.886e-06*α
3 + 2.583e-04*α
2 + -1.426e-03*α + 8.643e-03
Moment: Cm = f(α) = 8.333e-06*α
3 + 9.567e-05*α
2 + -5.128e-03*α + -9.816e-02
Lift: Cl = f(α) = -1.227e-04*α
3 + 7.790e-04*α
2 + 1.148e-01*α + 6.839e-01
Drag: Cd = f(α) = -7.583e-06*α
3 + 2.483e-04*α
2 + -9.242e-04*α + 6.495e-03
Moment: Cm = f(α) = 4.519e-06*α
3 + 8.888e-05*α
2 + -4.503e-03*α + -1.001e-01