MH 60 10.08% (mh60-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 60 10.08% (mh60-il) Reynolds number: 200,000 Max Cl/Cd: 61.4 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh60-il-200000.txt Download as CSV file: xf-mh60-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: MH 60 10.08%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4560 0.08509 0.08234 0.0011 1.0000 0.0524
-8.500 -0.4664 0.07874 0.07603 -0.0040 1.0000 0.0546
-8.250 -0.4910 0.07012 0.06749 -0.0141 1.0000 0.0557
-8.000 -0.5119 0.06327 0.06058 -0.0210 1.0000 0.0557
-7.750 -0.5296 0.05763 0.05470 -0.0258 1.0000 0.0561
-6.250 -0.5108 0.03016 0.02445 -0.0300 0.9854 0.0243
-6.000 -0.4790 0.02601 0.01993 -0.0318 0.9738 0.0226
-5.750 -0.4482 0.02298 0.01644 -0.0326 0.9621 0.0218
-5.500 -0.4197 0.02089 0.01402 -0.0325 0.9502 0.0214
-5.250 -0.3949 0.01934 0.01224 -0.0315 0.9382 0.0217
-5.000 -0.3729 0.01816 0.01089 -0.0298 0.9266 0.0227
-4.750 -0.3518 0.01730 0.00989 -0.0279 0.9155 0.0238
-4.500 -0.3327 0.01595 0.00854 -0.0262 0.9045 0.0282
-4.250 -0.3119 0.01507 0.00758 -0.0246 0.8943 0.0363
-4.000 -0.2923 0.01389 0.00645 -0.0226 0.8852 0.0690
-3.750 -0.2739 0.01248 0.00586 -0.0211 0.8755 0.2207
-3.500 -0.2511 0.01206 0.00567 -0.0202 0.8663 0.2958
-3.250 -0.2289 0.01177 0.00549 -0.0188 0.8583 0.3510
-3.000 -0.2053 0.01144 0.00532 -0.0179 0.8488 0.4134
-2.750 -0.1824 0.01113 0.00520 -0.0166 0.8402 0.4793
-2.500 -0.1603 0.01081 0.00506 -0.0151 0.8320 0.5435
-2.250 -0.1373 0.01048 0.00496 -0.0138 0.8227 0.6130
-2.000 -0.1158 0.01015 0.00485 -0.0118 0.8151 0.6877
-1.750 -0.0927 0.00982 0.00477 -0.0101 0.8059 0.7715
-1.500 -0.0616 0.00961 0.00473 -0.0097 0.7977 0.8614
-1.250 -0.0107 0.00957 0.00464 -0.0134 0.7898 0.9297
-1.000 0.0415 0.00959 0.00453 -0.0179 0.7805 0.9660
-0.750 0.0924 0.00959 0.00435 -0.0222 0.7721 0.9913
-0.500 0.1295 0.00954 0.00415 -0.0242 0.7619 1.0000
-0.250 0.1528 0.00952 0.00403 -0.0234 0.7514 1.0000
0.000 0.1762 0.00952 0.00391 -0.0224 0.7414 1.0000
0.250 0.1997 0.00952 0.00379 -0.0214 0.7316 1.0000
0.500 0.2246 0.00952 0.00372 -0.0207 0.7199 1.0000
0.750 0.2494 0.00954 0.00365 -0.0200 0.7085 1.0000
1.000 0.2743 0.00956 0.00359 -0.0193 0.6971 1.0000
1.250 0.2993 0.00958 0.00353 -0.0185 0.6855 1.0000
1.500 0.3244 0.00960 0.00346 -0.0177 0.6734 1.0000
1.750 0.3499 0.00963 0.00342 -0.0171 0.6602 1.0000
2.000 0.3756 0.00967 0.00340 -0.0165 0.6463 1.0000
2.250 0.4014 0.00971 0.00338 -0.0159 0.6318 1.0000
2.500 0.4273 0.00977 0.00339 -0.0153 0.6163 1.0000
2.750 0.4533 0.00984 0.00342 -0.0149 0.5994 1.0000
3.000 0.4794 0.00993 0.00346 -0.0144 0.5819 1.0000
3.250 0.5053 0.01004 0.00352 -0.0139 0.5640 1.0000
3.500 0.5312 0.01018 0.00358 -0.0133 0.5460 1.0000
3.750 0.5574 0.01033 0.00370 -0.0130 0.5256 1.0000
4.000 0.5833 0.01052 0.00380 -0.0125 0.5059 1.0000
4.250 0.6093 0.01072 0.00398 -0.0121 0.4855 1.0000
4.500 0.6352 0.01096 0.00415 -0.0118 0.4648 1.0000
4.750 0.6610 0.01122 0.00436 -0.0114 0.4447 1.0000
5.000 0.6868 0.01150 0.00460 -0.0111 0.4236 1.0000
5.250 0.7123 0.01182 0.00487 -0.0107 0.4036 1.0000
5.500 0.7379 0.01213 0.00517 -0.0104 0.3824 1.0000
5.750 0.7631 0.01250 0.00547 -0.0101 0.3625 1.0000
6.000 0.7884 0.01284 0.00582 -0.0097 0.3408 1.0000
6.250 0.8131 0.01326 0.00620 -0.0094 0.3205 1.0000
6.500 0.8379 0.01366 0.00661 -0.0090 0.2988 1.0000
6.750 0.8621 0.01414 0.00704 -0.0087 0.2785 1.0000
7.000 0.8863 0.01461 0.00751 -0.0083 0.2572 1.0000
7.250 0.9097 0.01516 0.00801 -0.0078 0.2371 1.0000
7.500 0.9330 0.01572 0.00860 -0.0074 0.2174 1.0000
7.750 0.9558 0.01631 0.00919 -0.0069 0.1988 1.0000
8.000 0.9778 0.01699 0.00982 -0.0064 0.1816 1.0000
8.250 0.9995 0.01768 0.01050 -0.0058 0.1648 1.0000
8.500 1.0209 0.01836 0.01122 -0.0052 0.1485 1.0000
8.750 1.0416 0.01908 0.01197 -0.0045 0.1329 1.0000
9.000 1.0614 0.01985 0.01278 -0.0038 0.1174 1.0000
9.250 1.0799 0.02072 0.01366 -0.0030 0.1029 1.0000
9.500 1.0968 0.02172 0.01466 -0.0021 0.0889 1.0000
9.750 1.1116 0.02287 0.01581 -0.0009 0.0757 1.0000
10.000 1.1242 0.02416 0.01711 0.0004 0.0634 1.0000
10.250 1.1356 0.02547 0.01850 0.0019 0.0537 1.0000
10.500 1.1428 0.02709 0.02019 0.0038 0.0467 1.0000
10.750 1.1449 0.02867 0.02175 0.0060 0.0413 1.0000
11.000 1.1480 0.03043 0.02369 0.0080 0.0373 1.0000
11.250 1.1521 0.03202 0.02535 0.0092 0.0330 1.0000
11.500 1.1492 0.03466 0.02802 0.0107 0.0297 1.0000
11.750 1.1539 0.03655 0.03010 0.0115 0.0269 1.0000
12.000 1.1550 0.03875 0.03238 0.0118 0.0241 1.0000
12.250 1.1484 0.04222 0.03589 0.0127 0.0217 1.0000
12.500 1.1489 0.04486 0.03875 0.0127 0.0198 1.0000
12.750 1.1483 0.04766 0.04169 0.0125 0.0183 1.0000
13.000 1.1456 0.05089 0.04502 0.0122 0.0173 1.0000
13.250 1.1371 0.05483 0.04900 0.0114 0.0157 1.0000
13.500 1.1298 0.05907 0.05342 0.0109 0.0152 1.0000
13.750 1.1251 0.06286 0.05744 0.0087 0.0142 1.0000
14.000 1.1170 0.06748 0.06225 0.0073 0.0139 1.0000
14.250 1.1095 0.07209 0.06703 0.0052 0.0135 1.0000
14.500 1.0984 0.07757 0.07271 0.0029 0.0135 1.0000
14.750 1.0873 0.08333 0.07865 0.0000 0.0132 1.0000
15.000 1.0762 0.08930 0.08475 -0.0035 0.0125 1.0000
15.250 1.0619 0.09620 0.09184 -0.0072 0.0126 1.0000
15.500 1.0454 0.10385 0.09968 -0.0114 0.0128 1.0000
15.750 1.0271 0.11230 0.10832 -0.0164 0.0131 1.0000
16.000 1.0078 0.12141 0.11760 -0.0218 0.0133 1.0000
16.250 0.9839 0.13209 0.12845 -0.0281 0.0139 1.0000
16.500 0.9589 0.14371 0.14018 -0.0348 0.0146 1.0000
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Polar data table (+)
Polar graphs
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