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 % Camber % Camber Chord % CL Max CD Min
1 2 3 4 5 Next > Last >>
NACA 6409 9.04 5.973 40 1.383 0
NACA 66-210 10 1.105 50 0.808 0
PRD 2C 8.66 3.399 30 1.091 0
NACA 671-215 14.98 1.111 50 0.803 0.0001
NACA 662-415 14.99 2.217 50 0.751 0.0001
Coordinates
XUpper YUpper XLower YLower
0 0 0 0
0.1 0.3 0.1 -0.15
0.2 0.5 0.2 -0.2
0.3 0.7 0.3 -0.3
0.4 0.8 0.4 -0.4
0.5 1 0.5 -0.5
1 1.6 1 -0.7
1.5 2 1.5 -0.9
2 2.4 2 -1
2.5 2.96 2.5 -1.11
5 4.3 5 -1.18
7.5 5.42 7.5 -1.08
10 6.31 10 -0.88
15 7.78 15 -0.36
20 8.88 20 0.17
25 9.58 25 0.7
30 10.13 30 1.12
40 10.35 40 1.65
50 9.81 50 1.86
60 8.78 60 1.92
70 7.28 70 1.76
80 5.34 80 1.36
90 2.95 90 0.74
100 0 100 0
X Y
1 0
0.9 0.0295
0.8 0.0534
0.7 0.0728
0.6 0.0878
0.5 0.0981
0.4 0.1035
0.3 0.1013
0.25 0.0958
0.2 0.0888
0.15 0.0778
0.1 0.0631
0.075 0.0542
0.05 0.043
0.025 0.0296
0.02 0.024
0.015 0.02
0.01 0.016
0.005 0.01
0.004 0.008
0.003 0.007
0.002 0.005
0.001 0.003
0 0
0 0
0.001 -0.0015
0.002 -0.002
0.003 -0.003
0.004 -0.004
0.005 -0.005
0.01 -0.007
0.015 -0.009
0.02 -0.01
0.025 -0.0111
0.05 -0.0118
0.075 -0.0108
0.1 -0.0088
0.15 -0.0036
0.2 0.0017
0.25 0.007
0.3 0.0112
0.4 0.0165
0.5 0.0186
0.6 0.0192
0.7 0.0176
0.8 0.0136
0.9 0.0074
1 0
X Y
100 0
90 2.95
80 5.34
70 7.28
60 8.78
50 9.81
40 10.35
30 10.13
25 9.58
20 8.88
15 7.78
10 6.31
7.5 5.42
5 4.3
2.5 2.96
2 2.4
1.5 2
1 1.6
0.5 1
0.4 0.8
0.3 0.7
0.2 0.5
0.1 0.3
0 0
0 0
0.1 -0.15
0.2 -0.2
0.3 -0.3
0.4 -0.4
0.5 -0.5
1 -0.7
1.5 -0.9
2 -1
2.5 -1.11
5 -1.18
7.5 -1.08
10 -0.88
15 -0.36
20 0.17
25 0.7
30 1.12
40 1.65
50 1.86
60 1.92
70 1.76
80 1.36
90 0.74
100 0
V 1.1