Joukowsky 13.00% thick 8.00% camber
Joukowsky 13.00% thick 8.00% camber
Curve fits of basic Javafoil data for Joukowsky 13.00% thick 8.00% camber, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -1.528e-04*α
3 + -1.069e-03*α
2 + 1.231e-01*α + 1.120e+00
Drag: Cd = f(α) = -4.203e-06*α
3 + 3.336e-04*α
2 + -7.550e-04*α + 6.599e-03
Moment: Cm = f(α) = 1.288e-05*α
3 + 3.440e-04*α
2 + -4.634e-03*α + -2.252e-01
Lift: Cl = f(α) = -1.516e-04*α
3 + -1.057e-03*α
2 + 1.233e-01*α + 1.124e+00
Drag: Cd = f(α) = -5.410e-06*α
3 + 2.978e-04*α
2 + -4.317e-04*α + 4.931e-03
Moment: Cm = f(α) = 9.085e-06*α
3 + 3.024e-04*α
2 + -3.623e-03*α + -2.275e-01
Lift: Cl = f(α) = -1.487e-04*α
3 + -1.024e-03*α
2 + 1.233e-01*α + 1.126e+00
Drag: Cd = f(α) = -7.230e-06*α
3 + 2.475e-04*α
2 + 4.145e-05*α + 3.896e-03
Moment: Cm = f(α) = 5.033e-06*α
3 + 2.548e-04*α
2 + -2.572e-03*α + -2.295e-01
Lift: Cl = f(α) = -1.470e-04*α
3 + -1.000e-03*α
2 + 1.234e-01*α + 1.127e+00
Drag: Cd = f(α) = -8.706e-06*α
3 + 2.173e-04*α
2 + 3.742e-04*α + 3.776e-03
Moment: Cm = f(α) = 2.603e-06*α
3 + 2.294e-04*α
2 + -1.990e-03*α + -2.305e-01