Airfoil:

mm

Job Status

Please wait while the PDF is generated...

Plot Number:

File:

Search for Airfoil
Winfoil Airfoils - Total Number: 277
Name T/C % T/C % Chord Position Camber % Camber Chord % CL Max CD Min
<< First < Prev 15 16 17 18 19 Next > Last >>
EPPLER 61 6.15 30 6.517 50 1.149 0.0005
EPPLER 62 (5.62%) 5.66 26.238 5.307 49.334 1.302 0.0058
FX 60-100 9.97 27.89 3.477 56.53 1.424 0.0062
FX63-137 13.67 30.87 5.84 56.53 2.199 0.0076
GOTTINGE.COR 13.75 30 4.409 40 1.699 0.016
Coordinates
XUpper YUpper XLower YLower
0 0.95 0 1.32
0.12 1.94 0.12 0.59
0.55 2.28 0.55 0.25
0.99 2.46 0.99 0.19
1.25 2.7 1.25 0
2.5 3.4 2.5 0.15
5 4.7 5 0.5
7.5 5.8 7.5 0.95
10 6.5 10 1.1
15 7.6 15 2
20 8.4 20 2.3
30 9.3 30 3.15
40 9.95 40 4
50 9.8 50 4.2
60 8.8 60 4.3
70 7.7 70 4
80 6 80 3.1
90 3.7 90 2
95 2.15 95 1
100 0 100 0
X Y
1 0
0.95 0.0215
0.9 0.037
0.8 0.06
0.7 0.077
0.6 0.088
0.5 0.098
0.4 0.0995
0.3 0.093
0.2 0.084
0.15 0.076
0.1 0.065
0.075 0.058
0.05 0.047
0.025 0.034
0.0125 0.027
0.0099 0.0246
0.0055 0.0228
0.0012 0.0194
0 0.0095
0 0.0132
0.0012 0.0059
0.0055 0.0025
0.0099 0.0019
0.0125 0
0.025 0.0015
0.05 0.005
0.075 0.0095
0.1 0.011
0.15 0.02
0.2 0.023
0.3 0.0315
0.4 0.04
0.5 0.042
0.6 0.043
0.7 0.04
0.8 0.031
0.9 0.02
0.95 0.01
1 0
X Y
100 0
95 2.15
90 3.7
80 6
70 7.7
60 8.8
50 9.8
40 9.95
30 9.3
20 8.4
15 7.6
10 6.5
7.5 5.8
5 4.7
2.5 3.4
1.25 2.7
0.99 2.46
0.55 2.28
0.12 1.94
0 0.95
0 1.32
0.12 0.59
0.55 0.25
0.99 0.19
1.25 0
2.5 0.15
5 0.5
7.5 0.95
10 1.1
15 2
20 2.3
30 3.15
40 4
50 4.2
60 4.3
70 4
80 3.1
90 2
95 1
100 0
V 1.1