Horten 18.00% thick 9.00% camber
Horten t/c=18.0%, f/c=9.0%
Curve fits of basic Javafoil data for Horten 18.00% thick 9.00% camber, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -9.152e-05*α
3 + 9.672e-04*α
2 + 1.123e-01*α + 3.989e-01
Drag: Cd = f(α) = -2.281e-06*α
3 + 2.962e-04*α
2 + -1.899e-03*α + 2.165e-02
Moment: Cm = f(α) = -9.895e-07*α
3 + -2.288e-05*α
2 + 3.432e-04*α + 1.005e-02
Lift: Cl = f(α) = -9.273e-05*α
3 + 9.467e-04*α
2 + 1.132e-01*α + 4.092e-01
Drag: Cd = f(α) = -1.950e-06*α
3 + 2.740e-04*α
2 + -1.893e-03*α + 1.797e-02
Moment: Cm = f(α) = -7.963e-07*α
3 + -2.727e-05*α
2 + 2.983e-04*α + 1.106e-02
Lift: Cl = f(α) = -9.416e-05*α
3 + 9.209e-04*α
2 + 1.142e-01*α + 4.198e-01
Drag: Cd = f(α) = -1.989e-06*α
3 + 2.570e-04*α
2 + -1.709e-03*α + 1.329e-02
Moment: Cm = f(α) = -5.647e-07*α
3 + -3.111e-05*α
2 + 2.347e-04*α + 1.206e-02
Lift: Cl = f(α) = -9.591e-05*α
3 + 9.237e-04*α
2 + 1.148e-01*α + 4.216e-01
Drag: Cd = f(α) = -2.341e-06*α
3 + 2.550e-04*α
2 + -1.526e-03*α + 1.060e-02
Moment: Cm = f(α) = -4.277e-07*α
3 + -3.303e-05*α
2 + 1.961e-04*α + 1.256e-02