Joukowsky 20.00% thick 3.00% camber
Joukowsky 20.00% thick 3.00% camber
Curve fits of basic Javafoil data for Joukowsky 20.00% thick 3.00% camber, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -9.536e-05*α
3 + -2.313e-04*α
2 + 1.244e-01*α + 4.491e-01
Drag: Cd = f(α) = -2.656e-06*α
3 + 2.438e-04*α
2 + 1.708e-04*α + 2.813e-03
Moment: Cm = f(α) = -1.770e-07*α
3 + 5.261e-05*α
2 + -2.128e-04*α + -8.624e-02
Lift: Cl = f(α) = -9.587e-05*α
3 + -2.282e-04*α
2 + 1.256e-01*α + 4.501e-01
Drag: Cd = f(α) = -2.601e-06*α
3 + 2.083e-04*α
2 + 2.309e-04*α + 1.756e-03
Moment: Cm = f(α) = -2.657e-07*α
3 + 4.840e-05*α
2 + -1.551e-04*α + -8.679e-02
Lift: Cl = f(α) = -9.577e-05*α
3 + -2.227e-04*α
2 + 1.268e-01*α + 4.497e-01
Drag: Cd = f(α) = -2.645e-06*α
3 + 1.657e-04*α
2 + 3.550e-04*α + 1.438e-03
Moment: Cm = f(α) = -4.093e-07*α
3 + 4.310e-05*α
2 + -7.439e-05*α + -8.731e-02
Lift: Cl = f(α) = -9.580e-05*α
3 + -2.187e-04*α
2 + 1.275e-01*α + 4.497e-01
Drag: Cd = f(α) = -2.671e-06*α
3 + 1.481e-04*α
2 + 4.023e-04*α + 1.367e-03
Moment: Cm = f(α) = -4.468e-07*α
3 + 4.096e-05*α
2 + -4.940e-05*α + -8.752e-02