NACA64-112 a=0.0
NACA64112a=0.0
Curve fits of basic Javafoil data for NACA64-112 a=0.0, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -3.130e-04*α
3 + 8.023e-04*α
2 + 1.220e-01*α + 4.996e-02
Drag: Cd = f(α) = -2.414e-05*α
3 + 3.443e-04*α
2 + 1.215e-04*α + 5.228e-03
Moment: Cm = f(α) = 2.120e-06*α
3 + -4.172e-06*α
2 + -1.150e-03*α + -7.592e-03
Lift: Cl = f(α) = -2.428e-04*α
3 + -1.150e-04*α
2 + 1.230e-01*α + 5.985e-02
Drag: Cd = f(α) = 1.638e-06*α
3 + 1.040e-04*α
2 + -7.072e-05*α + 6.563e-03
Moment: Cm = f(α) = 9.200e-07*α
3 + -4.460e-07*α
2 + -1.116e-03*α + -7.651e-03
Lift: Cl = f(α) = -2.524e-04*α
3 + -1.224e-04*α
2 + 1.240e-01*α + 6.054e-02
Drag: Cd = f(α) = 1.217e-06*α
3 + 7.693e-05*α
2 + -6.307e-05*α + 5.690e-03
Moment: Cm = f(α) = 5.807e-07*α
3 + -1.574e-06*α
2 + -1.103e-03*α + -7.633e-03
Lift: Cl = f(α) = -2.559e-04*α
3 + -5.696e-05*α
2 + 1.243e-01*α + 5.914e-02
Drag: Cd = f(α) = 6.893e-07*α
3 + 6.414e-05*α
2 + -3.375e-05*α + 5.360e-03
Moment: Cm = f(α) = 4.985e-07*α
3 + -1.133e-06*α
2 + -1.099e-03*α + -7.643e-03