GOE 277 (DAIMLER VIII)
GOE 277 (DAIMLER VIII) AIRFOIL
New! Bulk download of polars in Excel format:
goe277.xlsx Curve fits of basic Javafoil data for GOE 277 (DAIMLER VIII), smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -1.877e-04*α
3 + 1.012e-03*α
2 + 1.176e-01*α + 4.859e-01
Drag: Cd = f(α) = 5.510e-07*α
3 + 3.019e-04*α
2 + -2.578e-03*α + 1.904e-02
Moment: Cm = f(α) = 2.971e-05*α
3 + 6.734e-05*α
2 + -6.657e-03*α + -6.658e-02
Lift: Cl = f(α) = -1.986e-04*α
3 + 8.159e-04*α
2 + 1.178e-01*α + 4.952e-01
Drag: Cd = f(α) = 1.125e-06*α
3 + 2.953e-04*α
2 + -2.547e-03*α + 1.600e-02
Moment: Cm = f(α) = 2.492e-05*α
3 + 8.919e-05*α
2 + -6.231e-03*α + -7.038e-02
Lift: Cl = f(α) = -2.090e-04*α
3 + 6.374e-04*α
2 + 1.180e-01*α + 5.047e-01
Drag: Cd = f(α) = -4.377e-06*α
3 + 2.969e-04*α
2 + -1.758e-03*α + 1.000e-02
Moment: Cm = f(α) = 1.071e-05*α
3 + 1.276e-04*α
2 + -4.529e-03*α + -7.887e-02
Lift: Cl = f(α) = -2.160e-04*α
3 + 6.416e-04*α
2 + 1.189e-01*α + 5.022e-01
Drag: Cd = f(α) = -1.268e-05*α
3 + 2.951e-04*α
2 + -6.235e-04*α + 6.416e-03
Moment: Cm = f(α) = 1.316e-07*α
3 + 1.356e-04*α
2 + -3.103e-03*α + -8.297e-02