The 'PolarBrowser' application, a polar file converter is available
in the software section at:
http://www.MH-AeroTools.de/airfoils/
MH 104
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
0.01300
0.0154
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.01020
0.0129
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00980
0.0114
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00940
0.0097
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00830
0.0061
-99.999
-99.999
-99.999
-99.999
3.000
0.330
0.00840
0.0045
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00860
0.0031
-99.999
-99.999
-99.999
-99.999
5.000
0.540
0.00900
0.0020
-99.999
-99.999
-99.999
-99.999
6.000
0.640
0.00960
0.0012
-99.999
-99.999
-99.999
-99.999
7.000
0.740
0.01010
0.0015
-99.999
-99.999
-99.999
-99.999
8.000
0.830
0.01090
0.0047
-99.999
-99.999
-99.999
-99.999
10.000
0.920
0.01440
0.0187
-99.999
-99.999
-99.999
-99.999
12.000
0.980
0.02060
0.0256
-99.999
-99.999
-99.999
-99.999
14.001
1.040
0.02940
0.0244
-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
0.01220
0.0155
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.00950
0.0130
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00900
0.0114
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00870
0.0097
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00770
0.0060
-99.999
-99.999
-99.999
-99.999
3.000
0.330
0.00770
0.0042
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00780
0.0027
-99.999
-99.999
-99.999
-99.999
5.000
0.540
0.00820
0.0013
-99.999
-99.999
-99.999
-99.999
6.000
0.650
0.00860
0.0003
-99.999
-99.999
-99.999
-99.999
7.000
0.750
0.00910
-0.0004
-99.999
-99.999
-99.999
-99.999
8.000
0.850
0.00980
0.0003
-99.999
-99.999
-99.999
-99.999
10.000
0.950
0.01320
0.0155
-99.999
-99.999
-99.999
-99.999
12.001
1.000
0.01910
0.0251
-99.999
-99.999
-99.999
-99.999
14.001
1.060
0.02750
0.0251
-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
0.01150
0.0156
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.00870
0.0130
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00840
0.0114
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00820
0.0097
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00730
0.0060
-99.999
-99.999
-99.999
-99.999
3.000
0.330
0.00710
0.0040
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00720
0.0022
-99.999
-99.999
-99.999
-99.999
5.000
0.550
0.00740
0.0008
-99.999
-99.999
-99.999
-99.999
6.000
0.650
0.00780
-0.0005
-99.999
-99.999
-99.999
-99.999
7.000
0.760
0.00830
-0.0014
-99.999
-99.999
-99.999
-99.999
8.000
0.860
0.00910
-0.0015
-99.999
-99.999
-99.999
-99.999
10.000
0.980
0.01210
0.0120
-99.999
-99.999
-99.999
-99.999
12.001
1.030
0.01760
0.0245
-99.999
-99.999
-99.999
-99.999
14.001
1.080
0.02560
0.0260
-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
0.01340
0.0154
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.01100
0.0129
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.01070
0.0114
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.01040
0.0097
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.01030
0.0062
-99.999
-99.999
-99.999
-99.999
3.000
0.330
0.01030
0.0048
-99.999
-99.999
-99.999
-99.999
4.000
0.430
0.01040
0.0035
-99.999
-99.999
-99.999
-99.999
5.000
0.540
0.01050
0.0027
-99.999
-99.999
-99.999
-99.999
6.000
0.640
0.01120
0.0027
-99.999
-99.999
-99.999
-99.999
7.000
0.720
0.01210
0.0060
-99.999
-99.999
-99.999
-99.999
8.000
0.780
0.01320
0.0133
-99.999
-99.999
-99.999
-99.999
10.000
0.870
0.01680
0.0234
-99.999
-99.999
-99.999
-99.999
12.000
0.960
0.02220
0.0267
-99.999
-99.999
-99.999
-99.999
14.001
1.040
0.02940
0.0252
-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
0.01270
0.0155
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.01040
0.0130
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.01010
0.0114
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00990
0.0097
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00980
0.0060
-99.999
-99.999
-99.999
-99.999
3.000
0.330
0.00980
0.0044
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.01000
0.0031
-99.999
-99.999
-99.999
-99.999
5.000
0.540
0.01040
0.0023
-99.999
-99.999
-99.999
-99.999
6.000
0.640
0.01100
0.0021
-99.999
-99.999
-99.999
-99.999
7.000
0.730
0.01180
0.0040
-99.999
-99.999
-99.999
-99.999
8.000
0.790
0.01290
0.0117
-99.999
-99.999
-99.999
-99.999
10.000
0.890
0.01600
0.0225
-99.999
-99.999
-99.999
-99.999
12.000
0.970
0.02100
0.0267
-99.999
-99.999
-99.999
-99.999
14.001
1.060
0.02750
0.0260
-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
0.01200
0.0156
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.00990
0.0130
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00960
0.0114
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00950
0.0097
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00930
0.0060
-99.999
-99.999
-99.999
-99.999
3.000
0.330
0.00940
0.0042
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00980
0.0029
-99.999
-99.999
-99.999
-99.999
5.000
0.540
0.01030
0.0020
-99.999
-99.999
-99.999
-99.999
6.000
0.640
0.01080
0.0017
-99.999
-99.999
-99.999
-99.999
7.000
0.740
0.01160
0.0033
-99.999
-99.999
-99.999
-99.999
8.000
0.800
0.01270
0.0104
-99.999
-99.999
-99.999
-99.999
10.000
0.900
0.01540
0.0213
-99.999
-99.999
-99.999
-99.999
12.000
0.990
0.02020
0.0265
-99.999
-99.999
-99.999
-99.999
14.001
1.080
0.02570
0.0264
-99.999
-99.999
-99.999
-99.999