EPPLER 485
EPPLER 485 AIRFOIL
New! Bulk download of polars in Excel format:
e485.xlsx Curve fits of basic Javafoil data for EPPLER 485, smooth airfoils, Mach 0:
Re:
500k |
1M |
3M |
6MRe = 500k | 1M | 3M | 6M
Lift: Cl = f(α) = -2.677e-04*α
3 + 3.363e-04*α
2 + 1.269e-01*α + 1.187e-01
Drag: Cd = f(α) = 3.062e-06*α
3 + 1.579e-04*α
2 + -3.723e-04*α + 5.735e-03
Moment: Cm = f(α) = 1.496e-06*α
3 + -1.043e-06*α
2 + -1.281e-03*α + -1.427e-02
Lift: Cl = f(α) = -2.721e-04*α
3 + 4.957e-04*α
2 + 1.270e-01*α + 1.161e-01
Drag: Cd = f(α) = 4.060e-06*α
3 + 1.120e-04*α
2 + -3.863e-04*α + 5.316e-03
Moment: Cm = f(α) = 8.156e-07*α
3 + 9.721e-07*α
2 + -1.258e-03*α + -1.430e-02
Lift: Cl = f(α) = -2.699e-04*α
3 + 6.272e-04*α
2 + 1.270e-01*α + 1.133e-01
Drag: Cd = f(α) = 3.149e-06*α
3 + 8.716e-05*α
2 + -3.412e-04*α + 4.980e-03
Moment: Cm = f(α) = 2.304e-07*α
3 + -5.558e-07*α
2 + -1.234e-03*α + -1.427e-02
Lift: Cl = f(α) = -2.575e-04*α
3 + 6.408e-04*α
2 + 1.265e-01*α + 1.130e-01
Drag: Cd = f(α) = 6.116e-07*α
3 + 6.365e-05*α
2 + -1.824e-04*α + 5.102e-03
Moment: Cm = f(α) = 8.812e-09*α
3 + -1.679e-06*α
2 + -1.225e-03*α + -1.425e-02