NACA65-314 a=0.5
NACA65314a=0.5
Curve fits of basic Javafoil data for NACA65-314 a=0.5, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -2.128e-04*α
3 + 5.041e-04*α
2 + 1.173e-01*α + 2.346e-01
Drag: Cd = f(α) = -4.783e-06*α
3 + 3.983e-04*α
2 + -1.322e-03*α + 6.725e-03
Moment: Cm = f(α) = 7.371e-06*α
3 + 9.563e-05*α
2 + -2.607e-03*α + -4.033e-02
Lift: Cl = f(α) = -2.672e-04*α
3 + 2.784e-04*α
2 + 1.227e-01*α + 2.328e-01
Drag: Cd = f(α) = -1.656e-05*α
3 + 3.373e-04*α
2 + -4.284e-05*α + 3.919e-03
Moment: Cm = f(α) = -4.859e-07*α
3 + 5.862e-05*α
2 + -1.852e-03*α + -4.105e-02
Lift: Cl = f(α) = -2.339e-04*α
3 + -3.301e-04*α
2 + 1.251e-01*α + 2.397e-01
Drag: Cd = f(α) = 1.548e-06*α
3 + 8.643e-05*α
2 + 2.973e-05*α + 5.683e-03
Moment: Cm = f(α) = 5.811e-07*α
3 + 7.319e-06*α
2 + -1.567e-03*α + -4.080e-02
Lift: Cl = f(α) = -2.369e-04*α
3 + -2.893e-04*α
2 + 1.256e-01*α + 2.393e-01
Drag: Cd = f(α) = 8.917e-07*α
3 + 7.428e-05*α
2 + 6.305e-05*α + 5.259e-03
Moment: Cm = f(α) = 3.640e-07*α
3 + 8.340e-06*α
2 + -1.570e-03*α + -4.089e-02