Horten 19.00% thick 9.00% camber
Horten t/c=19.0%, f/c=9.0%
Curve fits of basic Javafoil data for Horten 19.00% thick 9.00% camber, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -8.559e-05*α
3 + 8.588e-04*α
2 + 1.131e-01*α + 4.085e-01
Drag: Cd = f(α) = -2.451e-06*α
3 + 2.943e-04*α
2 + -1.757e-03*α + 2.088e-02
Moment: Cm = f(α) = -8.899e-07*α
3 + -2.421e-05*α
2 + 3.192e-04*α + 1.124e-02
Lift: Cl = f(α) = -8.668e-05*α
3 + 8.408e-04*α
2 + 1.139e-01*α + 4.184e-01
Drag: Cd = f(α) = -2.196e-06*α
3 + 2.742e-04*α
2 + -1.730e-03*α + 1.672e-02
Moment: Cm = f(α) = -7.509e-07*α
3 + -2.756e-05*α
2 + 2.774e-04*α + 1.219e-02
Lift: Cl = f(α) = -8.886e-05*α
3 + 8.319e-04*α
2 + 1.151e-01*α + 4.252e-01
Drag: Cd = f(α) = -2.485e-06*α
3 + 2.584e-04*α
2 + -1.466e-03*α + 1.162e-02
Moment: Cm = f(α) = -4.712e-07*α
3 + -3.168e-05*α
2 + 1.917e-04*α + 1.335e-02
Lift: Cl = f(α) = -9.093e-05*α
3 + 8.356e-04*α
2 + 1.159e-01*α + 4.261e-01
Drag: Cd = f(α) = -2.849e-06*α
3 + 2.546e-04*α
2 + -1.279e-03*α + 9.324e-03
Moment: Cm = f(α) = -2.838e-07*α
3 + -3.322e-05*α
2 + 1.427e-04*α + 1.373e-02