MH 150 23.89%
MH 150 23.89%
New! Bulk download of polars in Excel format:
mh150.xlsx Curve fits of basic Javafoil data for MH 150 23.89%, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -9.443e-05*α
3 + -3.060e-04*α
2 + 1.255e-01*α + 8.694e-01
Drag: Cd = f(α) = -4.655e-06*α
3 + 1.857e-04*α
2 + 4.897e-04*α + 8.789e-03
Moment: Cm = f(α) = 3.002e-07*α
3 + 7.142e-05*α
2 + -1.191e-03*α + -1.603e-01
Lift: Cl = f(α) = -9.635e-05*α
3 + -3.204e-04*α
2 + 1.266e-01*α + 8.762e-01
Drag: Cd = f(α) = -3.771e-06*α
3 + 1.688e-04*α
2 + 3.720e-04*α + 6.519e-03
Moment: Cm = f(α) = 4.458e-07*α
3 + 7.073e-05*α
2 + -1.208e-03*α + -1.622e-01
Lift: Cl = f(α) = -9.681e-05*α
3 + -3.327e-04*α
2 + 1.275e-01*α + 8.816e-01
Drag: Cd = f(α) = -2.906e-06*α
3 + 1.448e-04*α
2 + 3.293e-04*α + 5.137e-03
Moment: Cm = f(α) = 5.678e-07*α
3 + 6.786e-05*α
2 + -1.180e-03*α + -1.637e-01
Lift: Cl = f(α) = -9.593e-05*α
3 + -3.357e-04*α
2 + 1.276e-01*α + 8.836e-01
Drag: Cd = f(α) = -2.488e-06*α
3 + 1.320e-04*α
2 + 3.323e-04*α + 4.904e-03
Moment: Cm = f(α) = 7.253e-07*α
3 + 6.707e-05*α
2 + -1.178e-03*α + -1.643e-01