NACA64-716 a=0.0
NACA64716a=0.0
Curve fits of basic Javafoil data for NACA64-716 a=0.0, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -2.116e-04*α
3 + 6.306e-04*α
2 + 1.214e-01*α + 4.166e-01
Drag: Cd = f(α) = -5.105e-07*α
3 + 3.522e-04*α
2 + -2.172e-03*α + 1.028e-02
Moment: Cm = f(α) = 4.449e-06*α
3 + 6.997e-05*α
2 + -2.660e-03*α + -4.866e-02
Lift: Cl = f(α) = -2.319e-04*α
3 + 6.819e-04*α
2 + 1.249e-01*α + 4.115e-01
Drag: Cd = f(α) = -1.014e-05*α
3 + 3.659e-04*α
2 + -7.117e-04*α + 3.161e-03
Moment: Cm = f(α) = -1.866e-06*α
3 + 8.473e-05*α
2 + -1.555e-03*α + -5.361e-02
Lift: Cl = f(α) = -2.420e-04*α
3 + 7.132e-04*α
2 + 1.273e-01*α + 4.075e-01
Drag: Cd = f(α) = -1.531e-05*α
3 + 3.319e-04*α
2 + 1.898e-04*α + 7.868e-04
Moment: Cm = f(α) = -4.029e-06*α
3 + 7.876e-05*α
2 + -1.153e-03*α + -5.465e-02
Lift: Cl = f(α) = -1.760e-04*α
3 + -1.085e-05*α
2 + 1.258e-01*α + 4.227e-01
Drag: Cd = f(α) = 3.424e-06*α
3 + 7.149e-05*α
2 + -1.896e-05*α + 5.521e-03
Moment: Cm = f(α) = 4.635e-07*α
3 + 9.363e-06*α
2 + -1.096e-03*α + -5.362e-02