GOE 229 (MVA H.39) AIRFOIL (goe229-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 229 (MVA H.39) AIRFOIL (goe229-il) Reynolds number: 100,000 Max Cl/Cd: 38.52 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe229-il-100000-n5.txt Download as CSV file: xf-goe229-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 229 (MVA H.39) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.1942 0.09270 0.08794 -0.1018 0.9572 0.0342
-11.750 -0.2268 0.08111 0.07623 -0.1102 0.9492 0.0336
-11.500 -0.2549 0.07114 0.06605 -0.1195 0.9420 0.0332
-11.250 -0.2765 0.06431 0.05901 -0.1255 0.9306 0.0331
-11.000 -0.2904 0.05848 0.05291 -0.1315 0.9209 0.0332
-10.750 -0.3021 0.05406 0.04824 -0.1354 0.9088 0.0335
-10.500 -0.3140 0.05072 0.04466 -0.1375 0.8960 0.0340
-10.250 -0.3172 0.04734 0.04092 -0.1414 0.8863 0.0347
-10.000 -0.3162 0.04480 0.03798 -0.1433 0.8760 0.0354
-9.750 -0.3062 0.04222 0.03506 -0.1447 0.8687 0.0363
-9.500 -0.2920 0.03999 0.03276 -0.1445 0.8609 0.0372
-9.250 -0.2702 0.03795 0.03057 -0.1454 0.8559 0.0382
-9.000 -0.2553 0.03656 0.02906 -0.1449 0.8475 0.0395
-8.750 -0.2334 0.03510 0.02744 -0.1453 0.8414 0.0415
-8.500 -0.2102 0.03372 0.02585 -0.1457 0.8358 0.0434
-8.250 -0.1911 0.03265 0.02462 -0.1449 0.8279 0.0447
-8.000 -0.1651 0.03145 0.02326 -0.1450 0.8228 0.0459
-7.750 -0.1469 0.03033 0.02224 -0.1434 0.8157 0.0482
-7.500 -0.1253 0.02948 0.02141 -0.1427 0.8089 0.0504
-7.250 -0.0986 0.02862 0.02051 -0.1427 0.8042 0.0525
-7.000 -0.0808 0.02812 0.01998 -0.1414 0.7955 0.0540
-6.750 -0.0549 0.02743 0.01917 -0.1416 0.7898 0.0566
-6.500 -0.0315 0.02661 0.01832 -0.1419 0.7832 0.0593
-6.250 -0.0073 0.02574 0.01738 -0.1427 0.7757 0.0619
-6.000 0.0239 0.02476 0.01622 -0.1445 0.7705 0.0650
-5.750 0.0480 0.02410 0.01545 -0.1451 0.7620 0.0688
-5.500 0.0784 0.02313 0.01446 -0.1469 0.7558 0.0774
-5.250 0.1080 0.02226 0.01357 -0.1484 0.7494 0.0978
-5.000 0.1366 0.02043 0.01246 -0.1515 0.7420 0.2379
-4.750 0.1680 0.02034 0.01257 -0.1522 0.7367 0.3253
-4.500 0.1944 0.02056 0.01271 -0.1519 0.7288 0.3556
-4.250 0.2244 0.02069 0.01264 -0.1523 0.7221 0.3787
-4.000 0.2540 0.02091 0.01271 -0.1525 0.7158 0.3959
-3.750 0.2792 0.02117 0.01294 -0.1518 0.7079 0.4039
-3.500 0.3101 0.02123 0.01282 -0.1522 0.7024 0.4159
-3.250 0.3356 0.02161 0.01314 -0.1517 0.6951 0.4298
-3.000 0.3613 0.02205 0.01362 -0.1508 0.6886 0.4413
-2.750 0.3923 0.02211 0.01352 -0.1512 0.6838 0.4519
-2.500 0.4155 0.02223 0.01363 -0.1505 0.6753 0.4562
-2.250 0.4456 0.02204 0.01328 -0.1511 0.6685 0.4608
-2.000 0.4728 0.02192 0.01297 -0.1514 0.6600 0.4663
-1.750 0.5005 0.02180 0.01278 -0.1513 0.6519 0.4695
-1.500 0.5254 0.02177 0.01270 -0.1509 0.6424 0.4728
-1.250 0.5539 0.02161 0.01239 -0.1510 0.6334 0.4769
-1.000 0.5784 0.02156 0.01224 -0.1507 0.6220 0.4818
-0.750 0.6040 0.02143 0.01196 -0.1504 0.6095 0.4858
-0.500 0.6280 0.02134 0.01176 -0.1496 0.5950 0.4887
-0.250 0.6517 0.02129 0.01158 -0.1489 0.5802 0.4924
0.000 0.6753 0.02131 0.01149 -0.1483 0.5669 0.4968
0.250 0.6996 0.02135 0.01140 -0.1480 0.5550 0.5016
0.500 0.7228 0.02141 0.01138 -0.1473 0.5428 0.5046
0.750 0.7448 0.02151 0.01137 -0.1464 0.5289 0.5078
1.000 0.7661 0.02166 0.01145 -0.1454 0.5152 0.5119
1.250 0.7881 0.02182 0.01154 -0.1447 0.5034 0.5166
1.500 0.8108 0.02198 0.01161 -0.1441 0.4931 0.5210
1.750 0.8313 0.02218 0.01181 -0.1431 0.4814 0.5242
2.000 0.8511 0.02241 0.01202 -0.1420 0.4683 0.5279
2.250 0.8697 0.02268 0.01223 -0.1408 0.4529 0.5322
2.500 0.8860 0.02300 0.01245 -0.1392 0.4337 0.5372
2.750 0.8999 0.02340 0.01278 -0.1372 0.4101 0.5409
3.000 0.9133 0.02392 0.01318 -0.1352 0.3803 0.5450
3.250 0.9107 0.02539 0.01414 -0.1313 0.3101 0.5488
3.500 0.9034 0.02750 0.01575 -0.1274 0.2454 0.5526
3.750 0.9123 0.02871 0.01681 -0.1256 0.2235 0.5569
4.000 0.9231 0.02979 0.01783 -0.1240 0.2087 0.5606
4.250 0.9344 0.03087 0.01887 -0.1225 0.1950 0.5654
4.500 0.9437 0.03216 0.02008 -0.1210 0.1663 0.5708
4.750 0.9431 0.03421 0.02189 -0.1187 0.1244 0.5755
5.000 0.9501 0.03572 0.02336 -0.1172 0.1158 0.5801
5.250 0.9611 0.03698 0.02465 -0.1161 0.1129 0.5859
5.500 0.9725 0.03828 0.02597 -0.1151 0.1105 0.5924
5.750 0.9833 0.03959 0.02735 -0.1141 0.1086 0.5975
6.000 0.9945 0.04092 0.02874 -0.1132 0.1072 0.6040
6.250 1.0060 0.04229 0.03016 -0.1124 0.1062 0.6114
6.500 1.0162 0.04373 0.03170 -0.1115 0.1049 0.6183
6.750 1.0263 0.04526 0.03330 -0.1106 0.1037 0.6269
7.000 1.0363 0.04679 0.03491 -0.1098 0.1028 0.6348
7.250 1.0466 0.04835 0.03655 -0.1091 0.1021 0.6445
7.500 1.0568 0.04992 0.03820 -0.1084 0.1016 0.6537
7.750 1.0676 0.05147 0.03987 -0.1079 0.1012 0.6645
8.000 1.0780 0.05307 0.04158 -0.1073 0.1009 0.6763
8.250 1.0883 0.05469 0.04332 -0.1067 0.1006 0.6894
8.500 1.0984 0.05635 0.04512 -0.1062 0.1003 0.7047
8.750 1.1082 0.05803 0.04695 -0.1057 0.1001 0.7233
9.000 1.1175 0.05968 0.04882 -0.1051 0.0999 0.7490
9.250 1.1216 0.06106 0.05055 -0.1034 0.0998 0.8605
9.500 1.1267 0.06289 0.05247 -0.1026 0.0997 1.0000
9.750 1.1363 0.06489 0.05451 -0.1025 0.0996 1.0000
10.000 1.1457 0.06691 0.05659 -0.1023 0.0996 1.0000
10.250 1.1547 0.06897 0.05871 -0.1021 0.0995 1.0000
10.500 1.1635 0.07107 0.06090 -0.1019 0.0995 1.0000
10.750 1.1720 0.07320 0.06311 -0.1018 0.0995 1.0000
11.000 1.1802 0.07538 0.06537 -0.1016 0.0995 1.0000
11.250 1.1883 0.07759 0.06767 -0.1015 0.0993 1.0000
11.500 1.1961 0.07985 0.07002 -0.1014 0.0980 1.0000
11.750 1.2030 0.08221 0.07246 -0.1013 0.0957 1.0000
12.000 1.2083 0.08478 0.07512 -0.1012 0.0927 1.0000
12.250 1.2140 0.08732 0.07773 -0.1012 0.0898 1.0000
12.500 1.2257 0.08912 0.07969 -0.1012 0.0852 1.0000
12.750 1.2196 0.09322 0.08373 -0.1013 0.0642 1.0000
13.000 1.2158 0.09713 0.08766 -0.1015 0.0625 1.0000
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