BOEING VERTOL V13006-.7
BOEING VERTOL V13006-.7 AIRFOIL
New! Bulk download of polars in Excel format:
v13006.xlsx Curve fits of basic Javafoil data for BOEING VERTOL V13006-.7, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -3.698e-04*α
3 + 4.573e-04*α
2 + 9.788e-02*α + 6.182e-02
Drag: Cd = f(α) = -2.519e-06*α
3 + 6.324e-04*α
2 + -2.637e-04*α + 1.788e-02
Moment: Cm = f(α) = -5.266e-07*α
3 + 3.960e-05*α
2 + -3.044e-04*α + -5.035e-03
Lift: Cl = f(α) = -4.059e-04*α
3 + 4.380e-04*α
2 + 1.005e-01*α + 6.490e-02
Drag: Cd = f(α) = -3.995e-06*α
3 + 6.614e-04*α
2 + -1.708e-04*α + 1.285e-02
Moment: Cm = f(α) = 2.080e-07*α
3 + 5.120e-05*α
2 + -3.843e-04*α + -5.939e-03
Lift: Cl = f(α) = -4.719e-04*α
3 + 1.698e-03*α
2 + 1.145e-01*α + 6.315e-02
Drag: Cd = f(α) = -2.923e-05*α
3 + 4.064e-04*α
2 + -5.210e-04*α + 6.183e-03
Moment: Cm = f(α) = -8.483e-07*α
3 + 1.889e-06*α
2 + -8.116e-04*α + -7.153e-03
Lift: Cl = f(α) = -4.245e-04*α
3 + 6.436e-04*α
2 + 1.199e-01*α + 6.872e-02
Drag: Cd = f(α) = 1.591e-06*α
3 + 3.734e-05*α
2 + -3.384e-05*α + 6.551e-03
Moment: Cm = f(α) = 8.593e-07*α
3 + -9.154e-06*α
2 + -8.650e-04*α + -7.362e-03