GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il) Reynolds number: 100,000 Max Cl/Cd: 43.42 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe223-il-100000.txt Download as CSV file: xf-goe223-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 223 (MVA H.34) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.1341 0.10320 0.09883 -0.0837 0.9420 0.2054
-8.750 -0.0897 0.09955 0.09510 -0.0866 0.9403 0.2155
-8.500 -0.1613 0.08718 0.08285 -0.0947 0.9269 0.1611
-8.250 -0.3743 0.05393 0.04844 -0.1215 0.8969 0.0889
-8.000 -0.3389 0.04836 0.04171 -0.1296 0.8924 0.0831
-7.750 -0.3265 0.04586 0.03900 -0.1289 0.8814 0.0824
-7.500 -0.2820 0.04278 0.03542 -0.1336 0.8774 0.0828
-7.250 -0.2604 0.04119 0.03349 -0.1336 0.8669 0.0835
-7.000 -0.2154 0.03883 0.03078 -0.1371 0.8625 0.0838
-6.750 -0.1824 0.03698 0.02877 -0.1382 0.8553 0.0843
-6.500 -0.1484 0.03511 0.02694 -0.1393 0.8482 0.0860
-6.250 -0.1014 0.03350 0.02535 -0.1423 0.8451 0.0898
-6.000 -0.0787 0.03276 0.02459 -0.1413 0.8343 0.0919
-5.750 -0.0375 0.03151 0.02334 -0.1427 0.8299 0.0946
-5.500 0.0053 0.03027 0.02213 -0.1442 0.8270 0.0982
-5.250 0.0244 0.02970 0.02169 -0.1429 0.8144 0.1031
-5.000 0.0678 0.02845 0.02036 -0.1453 0.8109 0.1126
-4.750 0.0926 0.02757 0.01948 -0.1459 0.7989 0.1245
-4.500 0.1393 0.02565 0.01867 -0.1508 0.7949 0.3667
-4.250 0.1601 0.02717 0.02014 -0.1481 0.7830 0.4064
-4.000 0.1938 0.02809 0.02103 -0.1467 0.7782 0.4332
-3.500 0.2468 0.02923 0.02206 -0.1436 0.7619 0.4631
-3.250 0.2645 0.02993 0.02279 -0.1408 0.7514 0.4715
-3.000 0.2949 0.03014 0.02292 -0.1400 0.7460 0.4862
-2.750 0.3192 0.03047 0.02314 -0.1392 0.7380 0.4987
-2.500 0.3390 0.03107 0.02381 -0.1360 0.7309 0.5086
-2.250 0.3695 0.03115 0.02382 -0.1348 0.7273 0.5238
-2.000 0.3880 0.03149 0.02406 -0.1345 0.7168 0.5355
-1.750 0.4162 0.03126 0.02379 -0.1334 0.7126 0.5413
-1.500 0.4430 0.03107 0.02350 -0.1343 0.7061 0.5451
-1.250 0.4727 0.03084 0.02310 -0.1363 0.6993 0.5508
-1.000 0.5072 0.03029 0.02243 -0.1377 0.6958 0.5549
-0.750 0.5285 0.03055 0.02266 -0.1373 0.6895 0.5583
-0.500 0.5532 0.03064 0.02268 -0.1377 0.6833 0.5624
-0.250 0.5928 0.03007 0.02190 -0.1405 0.6799 0.5688
0.000 0.6231 0.02987 0.02164 -0.1411 0.6762 0.5728
0.250 0.6328 0.03090 0.02274 -0.1394 0.6682 0.5761
0.500 0.6674 0.03055 0.02229 -0.1408 0.6646 0.5811
0.750 0.7099 0.02986 0.02141 -0.1436 0.6619 0.5877
1.000 0.7125 0.03132 0.02300 -0.1409 0.6534 0.5908
1.250 0.7451 0.03100 0.02263 -0.1416 0.6492 0.5960
1.500 0.7882 0.03019 0.02166 -0.1441 0.6462 0.6023
1.750 0.7942 0.03162 0.02317 -0.1421 0.6387 0.6064
2.000 0.8222 0.03156 0.02311 -0.1422 0.6339 0.6117
2.250 0.8664 0.03060 0.02201 -0.1445 0.6306 0.6193
2.500 0.8789 0.03163 0.02311 -0.1431 0.6241 0.6239
2.750 0.9029 0.03177 0.02327 -0.1428 0.6183 0.6293
3.000 0.9493 0.03067 0.02202 -0.1452 0.6146 0.6381
3.250 0.9639 0.03142 0.02287 -0.1437 0.6085 0.6435
3.500 0.9831 0.03200 0.02349 -0.1430 0.6026 0.6505
3.750 1.0218 0.03144 0.02288 -0.1446 0.5992 0.6585
4.000 1.0660 0.03066 0.02201 -0.1467 0.5964 0.6679
4.250 1.0564 0.03289 0.02445 -0.1427 0.5878 0.6738
4.500 1.0938 0.03226 0.02382 -0.1438 0.5837 0.6841
4.750 1.1418 0.03117 0.02265 -0.1463 0.5805 0.6958
5.000 1.1344 0.03317 0.02484 -0.1424 0.5719 0.7040
5.250 1.1784 0.03203 0.02366 -0.1441 0.5668 0.7170
5.500 1.2099 0.03177 0.02342 -0.1445 0.5614 0.7309
5.750 1.2168 0.03281 0.02460 -0.1421 0.5541 0.7436
6.000 1.2616 0.03175 0.02352 -0.1440 0.5494 0.7636
6.250 1.2773 0.03235 0.02425 -0.1426 0.5435 0.7828
6.500 1.2877 0.03305 0.02514 -0.1404 0.5370 0.8066
6.750 1.3245 0.03207 0.02430 -0.1410 0.5327 0.8590
7.000 1.3379 0.03279 0.02518 -0.1396 0.5264 1.0000
7.250 1.3569 0.03358 0.02597 -0.1393 0.5194 1.0000
7.500 1.4100 0.03276 0.02499 -0.1429 0.5147 1.0000
7.750 1.4015 0.03462 0.02701 -0.1386 0.5068 1.0000
8.000 1.4326 0.03458 0.02695 -0.1392 0.5007 1.0000
8.250 1.4780 0.03404 0.02631 -0.1415 0.4955 1.0000
8.500 1.4545 0.03616 0.02864 -0.1350 0.4865 1.0000
8.750 1.5083 0.03514 0.02754 -0.1383 0.4811 1.0000
9.000 1.4814 0.03736 0.02995 -0.1314 0.4721 1.0000
9.250 1.5212 0.03662 0.02918 -0.1327 0.4654 1.0000
9.500 1.5055 0.03846 0.03115 -0.1276 0.4563 1.0000
9.750 1.5376 0.03789 0.03057 -0.1277 0.4488 1.0000
10.000 1.5168 0.04019 0.03302 -0.1226 0.4389 1.0000
10.250 1.5528 0.03935 0.03216 -0.1230 0.4319 1.0000
10.500 1.5230 0.04248 0.03546 -0.1177 0.4210 1.0000
10.750 1.5752 0.04036 0.03326 -0.1193 0.4144 1.0000
11.000 1.5345 0.04459 0.03768 -0.1137 0.4027 1.0000
11.250 1.5350 0.04613 0.03929 -0.1115 0.3931 1.0000
11.500 1.5613 0.04534 0.03845 -0.1109 0.3837 1.0000
11.750 1.5348 0.04943 0.04268 -0.1075 0.3725 1.0000
12.000 1.5382 0.05092 0.04419 -0.1059 0.3625 1.0000
12.250 1.5590 0.05068 0.04389 -0.1051 0.3524 1.0000
12.500 1.5374 0.05498 0.04833 -0.1028 0.3421 1.0000
12.750 1.5423 0.05661 0.04996 -0.1016 0.3324 1.0000
13.000 1.5531 0.05765 0.05097 -0.1006 0.3231 1.0000
13.250 1.5422 0.06131 0.05474 -0.0993 0.3139 1.0000
13.500 1.5543 0.06225 0.05562 -0.0984 0.3044 1.0000
13.750 1.5488 0.06540 0.05883 -0.0974 0.2951 1.0000
14.000 1.5495 0.06786 0.06132 -0.0965 0.2860 1.0000
14.250 1.5639 0.06856 0.06193 -0.0956 0.2769 1.0000
14.500 1.5522 0.07278 0.06630 -0.0950 0.2688 1.0000
14.750 1.5615 0.07413 0.06757 -0.0942 0.2592 1.0000
15.000 1.5523 0.07812 0.07167 -0.0938 0.2508 1.0000
15.250 1.5558 0.08034 0.07389 -0.0932 0.2422 1.0000
15.500 1.5502 0.08388 0.07749 -0.0929 0.2334 1.0000
15.750 1.5438 0.08763 0.08132 -0.0928 0.2249 1.0000
16.000 1.5423 0.09069 0.08440 -0.0927 0.2166 1.0000
16.250 1.5309 0.09539 0.08926 -0.0931 0.2090 1.0000
16.500 1.5261 0.09904 0.09294 -0.0934 0.2007 1.0000
16.750 1.5124 0.10433 0.09842 -0.0943 0.1936 1.0000
17.000 1.5035 0.10885 0.10300 -0.0952 0.1852 1.0000
17.250 1.4856 0.11509 0.10948 -0.0968 0.1773 1.0000
17.500 1.4747 0.12019 0.11469 -0.0982 0.1690 1.0000
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