MH 23 8% (mh23-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 23 8% (mh23-il) Reynolds number: 100,000 Max Cl/Cd: 49.99 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh23-il-100000.txt Download as CSV file: xf-mh23-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: MH 23 8%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4955 0.10216 0.09726 -0.0253 1.0000 0.0806
-9.000 -0.5100 0.09915 0.09434 -0.0305 1.0000 0.0814
-8.750 -0.5267 0.09583 0.09110 -0.0350 1.0000 0.0816
-8.500 -0.4913 0.09100 0.08624 -0.0268 1.0000 0.0869
-8.250 -0.4948 0.08768 0.08299 -0.0279 1.0000 0.0900
-8.000 -0.5084 0.08448 0.07987 -0.0301 1.0000 0.0922
-7.750 -0.5301 0.08175 0.07719 -0.0316 1.0000 0.0938
-7.500 -0.5555 0.07977 0.07509 -0.0325 1.0000 0.0948
-7.250 -0.5429 0.07471 0.07020 -0.0296 1.0000 0.0976
-7.000 -0.5403 0.07203 0.06755 -0.0274 1.0000 0.1012
-6.750 -0.5521 0.06940 0.06480 -0.0270 1.0000 0.1067
-6.500 -0.5593 0.06572 0.06105 -0.0256 1.0000 0.1102
-6.250 -0.5517 0.06289 0.05828 -0.0231 1.0000 0.1149
-6.000 -0.5584 0.05987 0.05501 -0.0220 1.0000 0.1234
-5.750 -0.5494 0.05693 0.05214 -0.0196 1.0000 0.1292
-5.500 -0.5471 0.05387 0.04895 -0.0179 1.0000 0.1391
-4.250 -0.4746 0.03263 0.02515 -0.0072 1.0000 0.0525
-4.000 -0.4532 0.02996 0.02164 -0.0041 1.0000 0.0435
-3.750 -0.4324 0.02725 0.01867 -0.0024 1.0000 0.0413
-3.500 -0.4104 0.02491 0.01601 -0.0009 1.0000 0.0396
-3.250 -0.3865 0.02295 0.01374 0.0007 1.0000 0.0388
-3.000 -0.3621 0.02127 0.01184 0.0021 1.0000 0.0387
-2.750 -0.3390 0.01995 0.01040 0.0035 1.0000 0.0400
-2.500 -0.1452 0.01416 0.00799 -0.0246 1.0000 1.0000
-2.250 -0.1352 0.01405 0.00764 -0.0218 1.0000 1.0000
-2.000 -0.1241 0.01398 0.00734 -0.0190 1.0000 1.0000
-1.750 -0.1122 0.01395 0.00711 -0.0164 1.0000 1.0000
-1.500 -0.0995 0.01394 0.00692 -0.0140 1.0000 1.0000
-1.250 -0.0863 0.01397 0.00673 -0.0116 1.0000 1.0000
-1.000 -0.0725 0.01401 0.00663 -0.0093 1.0000 1.0000
-0.750 -0.0584 0.01409 0.00658 -0.0071 1.0000 1.0000
-0.500 -0.0440 0.01419 0.00656 -0.0051 1.0000 1.0000
-0.250 -0.0293 0.01432 0.00658 -0.0031 1.0000 1.0000
0.000 -0.0144 0.01448 0.00665 -0.0011 1.0000 1.0000
0.250 0.0005 0.01467 0.00673 0.0007 1.0000 1.0000
0.500 0.0155 0.01490 0.00689 0.0025 1.0000 1.0000
0.750 0.0304 0.01516 0.00710 0.0041 1.0000 1.0000
1.000 0.0453 0.01546 0.00736 0.0057 1.0000 1.0000
1.250 0.0696 0.01587 0.00776 0.0053 0.9975 1.0000
1.500 0.1269 0.01656 0.00847 -0.0016 0.9850 1.0000
1.750 0.1840 0.01712 0.00909 -0.0082 0.9717 1.0000
2.000 0.2409 0.01752 0.00957 -0.0145 0.9576 1.0000
2.250 0.2987 0.01774 0.00992 -0.0207 0.9433 1.0000
2.500 0.3536 0.01774 0.01010 -0.0260 0.9273 1.0000
2.750 0.4064 0.01753 0.01007 -0.0305 0.9096 1.0000
3.000 0.4696 0.01700 0.00979 -0.0366 0.8928 1.0000
3.250 0.5201 0.01625 0.00939 -0.0398 0.8718 1.0000
3.500 0.5604 0.01538 0.00875 -0.0405 0.8462 1.0000
3.750 0.5933 0.01454 0.00811 -0.0396 0.8132 1.0000
4.000 0.6267 0.01377 0.00747 -0.0386 0.7657 1.0000
4.250 0.6585 0.01337 0.00706 -0.0373 0.6939 1.0000
4.500 0.6809 0.01362 0.00700 -0.0349 0.6020 1.0000
4.750 0.6968 0.01429 0.00725 -0.0318 0.5066 1.0000
5.000 0.7097 0.01518 0.00769 -0.0286 0.4115 1.0000
5.250 0.7214 0.01625 0.00828 -0.0256 0.3201 1.0000
5.500 0.7325 0.01753 0.00906 -0.0227 0.2358 1.0000
5.750 0.7436 0.01902 0.01006 -0.0199 0.1652 1.0000
6.000 0.7565 0.02068 0.01142 -0.0171 0.1188 1.0000
6.250 0.7712 0.02224 0.01277 -0.0149 0.0901 1.0000
6.500 0.7909 0.02444 0.01487 -0.0131 0.0755 1.0000
6.750 0.8142 0.02643 0.01707 -0.0116 0.0665 1.0000
7.000 0.8330 0.02835 0.01932 -0.0099 0.0555 1.0000
7.250 0.8539 0.03214 0.02331 -0.0083 0.0501 1.0000
7.500 0.8684 0.03409 0.02578 -0.0055 0.0434 1.0000
7.750 0.8776 0.03808 0.02997 -0.0032 0.0383 1.0000
8.000 0.8849 0.04152 0.03401 0.0004 0.0376 1.0000
8.250 0.8887 0.04524 0.03823 0.0038 0.0374 1.0000
8.500 0.8887 0.04891 0.04235 0.0073 0.0371 1.0000
8.750 0.8849 0.05256 0.04642 0.0107 0.0367 1.0000
9.000 0.8789 0.05643 0.05060 0.0138 0.0370 1.0000
9.250 0.8668 0.05997 0.05446 0.0170 0.0364 1.0000
9.500 0.8561 0.06402 0.05865 0.0194 0.0374 1.0000
9.750 0.8398 0.06751 0.06228 0.0222 0.0377 1.0000
10.000 0.8252 0.07159 0.06643 0.0237 0.0382 1.0000
10.250 0.7035 0.07088 0.06638 0.0242 0.0472 1.0000
10.500 0.6834 0.07722 0.07276 0.0211 0.0481 1.0000
10.750 0.6665 0.08425 0.07980 0.0176 0.0490 1.0000
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Polar data table (+)
Polar graphs
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