Joukowsky 16.00% thick 7.00% camber
Joukowsky 16.00% thick 7.00% camber
Curve fits of basic Javafoil data for Joukowsky 16.00% thick 7.00% camber, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -1.190e-04*α
3 + -7.047e-04*α
2 + 1.236e-01*α + 1.008e+00
Drag: Cd = f(α) = -5.856e-06*α
3 + 2.849e-04*α
2 + -1.174e-04*α + 6.036e-03
Moment: Cm = f(α) = 3.230e-06*α
3 + 1.890e-04*α
2 + -2.283e-03*α + -1.982e-01
Lift: Cl = f(α) = -1.182e-04*α
3 + -6.968e-04*α
2 + 1.241e-01*α + 1.011e+00
Drag: Cd = f(α) = -6.534e-06*α
3 + 2.502e-04*α
2 + 1.494e-04*α + 4.367e-03
Moment: Cm = f(α) = 1.749e-06*α
3 + 1.708e-04*α
2 + -1.751e-03*α + -2.002e-01
Lift: Cl = f(α) = -1.175e-04*α
3 + -6.875e-04*α
2 + 1.246e-01*α + 1.013e+00
Drag: Cd = f(α) = -7.396e-06*α
3 + 2.079e-04*α
2 + 5.334e-04*α + 3.298e-03
Moment: Cm = f(α) = -1.764e-07*α
3 + 1.451e-04*α
2 + -1.146e-03*α + -2.016e-01
Lift: Cl = f(α) = -1.167e-04*α
3 + -6.735e-04*α
2 + 1.249e-01*α + 1.013e+00
Drag: Cd = f(α) = -8.018e-06*α
3 + 1.858e-04*α
2 + 7.517e-04*α + 3.081e-03
Moment: Cm = f(α) = -1.077e-06*α
3 + 1.344e-04*α
2 + -8.471e-04*α + -2.024e-01