The 'PolarBrowser' application, a polar file converter is available
in the software section at:
http://www.MH-AeroTools.de/airfoils/
MH 106
smooth surface (r=0)
Copyright 2000-2004 Martin Hepperle
polar
500000.0
0.00000
Alpha
Cl
Cd
Cm
TU
TL
SU
SL
-4.000
-0.440
0.01040
0.0253
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.00960
0.0227
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00930
0.0213
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00840
0.0198
-99.999
-99.999
-99.999
-99.999
1.000
0.110
0.00810
0.0183
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00800
0.0168
-99.999
-99.999
-99.999
-99.999
3.000
0.330
0.00810
0.0152
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00840
0.0135
-99.999
-99.999
-99.999
-99.999
5.000
0.550
0.00880
0.0123
-99.999
-99.999
-99.999
-99.999
6.000
0.660
0.00940
0.0114
-99.999
-99.999
-99.999
-99.999
7.000
0.760
0.01080
0.0117
-99.999
-99.999
-99.999
-99.999
8.000
0.830
0.01370
0.0186
-99.999
-99.999
-99.999
-99.999
9.000
0.840
0.01610
0.0322
-99.999
-99.999
-99.999
-99.999
10.000
0.830
0.01920
0.0395
-99.999
-99.999
-99.999
-99.999
polar
700000.0
0.00000
Alpha
Cl
Cd
Cm
TU
TL
SU
SL
-4.000
-0.440
0.00960
0.0254
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.00900
0.0227
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00860
0.0213
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00790
0.0198
-99.999
-99.999
-99.999
-99.999
1.000
0.110
0.00760
0.0183
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00750
0.0168
-99.999
-99.999
-99.999
-99.999
3.000
0.330
0.00750
0.0152
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00760
0.0136
-99.999
-99.999
-99.999
-99.999
5.000
0.550
0.00790
0.0120
-99.999
-99.999
-99.999
-99.999
6.000
0.660
0.00850
0.0110
-99.999
-99.999
-99.999
-99.999
7.000
0.760
0.00980
0.0108
-99.999
-99.999
-99.999
-99.999
8.000
0.850
0.01260
0.0147
-99.999
-99.999
-99.999
-99.999
9.000
0.870
0.01490
0.0288
-99.999
-99.999
-99.999
-99.999
10.000
0.860
0.01800
0.0386
-99.999
-99.999
-99.999
-99.999
polar
1000000.0
0.00000
Alpha
Cl
Cd
Cm
TU
TL
SU
SL
-4.000
-0.440
0.00880
0.0254
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.00840
0.0227
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00810
0.0213
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00760
0.0198
-99.999
-99.999
-99.999
-99.999
1.000
0.110
0.00720
0.0183
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00700
0.0168
-99.999
-99.999
-99.999
-99.999
3.000
0.330
0.00700
0.0152
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00700
0.0136
-99.999
-99.999
-99.999
-99.999
5.000
0.550
0.00710
0.0120
-99.999
-99.999
-99.999
-99.999
6.000
0.660
0.00780
0.0106
-99.999
-99.999
-99.999
-99.999
7.000
0.760
0.00890
0.0102
-99.999
-99.999
-99.999
-99.999
8.000
0.860
0.01160
0.0126
-99.999
-99.999
-99.999
-99.999
9.000
0.900
0.01380
0.0245
-99.999
-99.999
-99.999
-99.999
10.000
0.880
0.01680
0.0372
-99.999
-99.999
-99.999
-99.999
rough surface (r=3)
Copyright 2000-2004 Martin Hepperle
polar
500000.0
0.00000
Alpha
Cl
Cd
Cm
TU
TL
SU
SL
-4.000
-0.440
0.01140
0.0252
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.01060
0.0227
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.01030
0.0213
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.01020
0.0198
-99.999
-99.999
-99.999
-99.999
1.000
0.110
0.01000
0.0183
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00990
0.0168
-99.999
-99.999
-99.999
-99.999
3.000
0.330
0.00970
0.0152
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00990
0.0138
-99.999
-99.999
-99.999
-99.999
5.000
0.550
0.01060
0.0130
-99.999
-99.999
-99.999
-99.999
6.000
0.650
0.01160
0.0128
-99.999
-99.999
-99.999
-99.999
7.000
0.750
0.01300
0.0142
-99.999
-99.999
-99.999
-99.999
8.000
0.800
0.01450
0.0228
-99.999
-99.999
-99.999
-99.999
9.000
0.830
0.01630
0.0333
-99.999
-99.999
-99.999
-99.999
10.000
0.830
0.01930
0.0402
-99.999
-99.999
-99.999
-99.999
polar
700000.0
0.00000
Alpha
Cl
Cd
Cm
TU
TL
SU
SL
-4.000
-0.440
0.01080
0.0253
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.01000
0.0227
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00980
0.0213
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00970
0.0198
-99.999
-99.999
-99.999
-99.999
1.000
0.110
0.00960
0.0183
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00950
0.0168
-99.999
-99.999
-99.999
-99.999
3.000
0.330
0.00960
0.0152
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00980
0.0137
-99.999
-99.999
-99.999
-99.999
5.000
0.550
0.01040
0.0128
-99.999
-99.999
-99.999
-99.999
6.000
0.650
0.01140
0.0126
-99.999
-99.999
-99.999
-99.999
7.000
0.750
0.01250
0.0133
-99.999
-99.999
-99.999
-99.999
8.000
0.820
0.01400
0.0199
-99.999
-99.999
-99.999
-99.999
9.000
0.850
0.01560
0.0311
-99.999
-99.999
-99.999
-99.999
10.000
0.860
0.01810
0.0391
-99.999
-99.999
-99.999
-99.999
polar
1000000.0
0.00000
Alpha
Cl
Cd
Cm
TU
TL
SU
SL
-4.000
-0.440
0.01030
0.0254
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.00950
0.0227
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00940
0.0213
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00930
0.0198
-99.999
-99.999
-99.999
-99.999
1.000
0.110
0.00910
0.0183
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00920
0.0168
-99.999
-99.999
-99.999
-99.999
3.000
0.330
0.00940
0.0152
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00970
0.0136
-99.999
-99.999
-99.999
-99.999
5.000
0.550
0.01030
0.0127
-99.999
-99.999
-99.999
-99.999
6.000
0.650
0.01120
0.0123
-99.999
-99.999
-99.999
-99.999
7.000
0.750
0.01220
0.0128
-99.999
-99.999
-99.999
-99.999
8.000
0.840
0.01340
0.0159
-99.999
-99.999
-99.999
-99.999
9.000
0.870
0.01480
0.0279
-99.999
-99.999
-99.999
-99.999
10.000
0.880
0.01700
0.0374
-99.999
-99.999
-99.999
-99.999