GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il) Reynolds number: 200,000 Max Cl/Cd: 67 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe223-il-200000-n5.txt Download as CSV file: xf-goe223-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3155 0.07893 0.07492 -0.1038 0.9314 0.0256
-12.750 -0.3511 0.06955 0.06532 -0.1107 0.9221 0.0255
-12.500 -0.3780 0.06255 0.05809 -0.1160 0.9128 0.0255
-12.250 -0.3998 0.05670 0.05200 -0.1207 0.9020 0.0256
-12.000 -0.4179 0.05165 0.04667 -0.1249 0.8922 0.0258
-11.750 -0.4327 0.04723 0.04193 -0.1289 0.8824 0.0261
-11.250 -0.4369 0.04123 0.03550 -0.1338 0.8662 0.0267
-11.000 -0.4253 0.03913 0.03329 -0.1357 0.8594 0.0271
-10.750 -0.4110 0.03727 0.03131 -0.1373 0.8527 0.0275
-10.500 -0.3954 0.03553 0.02939 -0.1385 0.8475 0.0280
-10.250 -0.3786 0.03395 0.02765 -0.1396 0.8405 0.0287
-10.000 -0.3606 0.03239 0.02585 -0.1406 0.8343 0.0296
-9.750 -0.3411 0.03091 0.02408 -0.1415 0.8284 0.0304
-9.500 -0.3201 0.02963 0.02251 -0.1423 0.8220 0.0311
-9.250 -0.2977 0.02829 0.02099 -0.1426 0.8172 0.0316
-9.000 -0.2747 0.02706 0.01974 -0.1425 0.8130 0.0323
-8.750 -0.2514 0.02611 0.01878 -0.1427 0.8074 0.0331
-8.500 -0.2272 0.02524 0.01784 -0.1428 0.8021 0.0340
-8.250 -0.2023 0.02439 0.01688 -0.1429 0.7976 0.0349
-8.000 -0.1779 0.02362 0.01604 -0.1430 0.7915 0.0355
-7.750 -0.1529 0.02288 0.01522 -0.1430 0.7857 0.0361
-7.500 -0.1268 0.02222 0.01443 -0.1432 0.7809 0.0368
-7.250 -0.1019 0.02151 0.01370 -0.1433 0.7749 0.0376
-7.000 -0.0773 0.02070 0.01293 -0.1435 0.7689 0.0385
-6.750 -0.0508 0.02002 0.01220 -0.1439 0.7637 0.0393
-6.500 -0.0245 0.01941 0.01157 -0.1444 0.7569 0.0400
-6.250 0.0028 0.01881 0.01091 -0.1450 0.7501 0.0407
-6.000 0.0307 0.01824 0.01027 -0.1457 0.7434 0.0415
-5.750 0.0586 0.01774 0.00969 -0.1464 0.7352 0.0427
-5.500 0.0873 0.01729 0.00912 -0.1471 0.7280 0.0438
-5.250 0.1156 0.01677 0.00854 -0.1478 0.7192 0.0450
-5.000 0.1446 0.01633 0.00798 -0.1485 0.7113 0.0462
-4.750 0.1731 0.01598 0.00755 -0.1491 0.7015 0.0477
-4.500 0.2019 0.01568 0.00714 -0.1495 0.6920 0.0495
-4.250 0.2305 0.01543 0.00677 -0.1499 0.6812 0.0519
-4.000 0.2591 0.01512 0.00644 -0.1504 0.6692 0.0585
-3.750 0.2879 0.01458 0.00601 -0.1512 0.6569 0.1130
-3.500 0.3169 0.01350 0.00555 -0.1528 0.6444 0.2953
-3.250 0.3449 0.01352 0.00555 -0.1529 0.6318 0.3317
-3.000 0.3728 0.01359 0.00552 -0.1529 0.6192 0.3490
-2.750 0.4004 0.01369 0.00549 -0.1529 0.6071 0.3623
-2.500 0.4279 0.01382 0.00548 -0.1529 0.5961 0.3745
-2.250 0.4552 0.01396 0.00552 -0.1528 0.5855 0.3835
-2.000 0.4827 0.01412 0.00551 -0.1528 0.5758 0.3938
-1.750 0.5094 0.01430 0.00562 -0.1526 0.5667 0.4024
-1.500 0.5369 0.01445 0.00564 -0.1526 0.5584 0.4102
-1.250 0.5637 0.01463 0.00576 -0.1525 0.5510 0.4180
-1.000 0.5911 0.01483 0.00586 -0.1525 0.5442 0.4283
-0.750 0.6179 0.01498 0.00598 -0.1523 0.5374 0.4345
-0.500 0.6449 0.01514 0.00604 -0.1523 0.5316 0.4387
-0.250 0.6726 0.01522 0.00608 -0.1524 0.5264 0.4425
0.000 0.7002 0.01533 0.00610 -0.1525 0.5216 0.4462
0.250 0.7273 0.01544 0.00617 -0.1526 0.5171 0.4489
0.500 0.7546 0.01556 0.00626 -0.1526 0.5131 0.4518
0.750 0.7819 0.01566 0.00636 -0.1527 0.5087 0.4552
1.000 0.8091 0.01578 0.00646 -0.1527 0.5045 0.4592
1.250 0.8362 0.01593 0.00654 -0.1527 0.5006 0.4633
1.500 0.8630 0.01609 0.00666 -0.1527 0.4967 0.4665
1.750 0.8895 0.01617 0.00680 -0.1527 0.4921 0.4698
2.000 0.9156 0.01631 0.00694 -0.1525 0.4868 0.4735
2.250 0.9414 0.01648 0.00707 -0.1524 0.4819 0.4779
2.500 0.9674 0.01663 0.00721 -0.1522 0.4772 0.4824
2.750 0.9930 0.01674 0.00740 -0.1520 0.4725 0.4863
3.000 1.0187 0.01689 0.00758 -0.1518 0.4685 0.4906
3.250 1.0443 0.01707 0.00775 -0.1517 0.4650 0.4953
3.500 1.0697 0.01725 0.00793 -0.1515 0.4614 0.5000
3.750 1.0947 0.01738 0.00816 -0.1512 0.4568 0.5045
4.000 1.1190 0.01754 0.00838 -0.1508 0.4520 0.5101
4.250 1.1430 0.01775 0.00859 -0.1503 0.4478 0.5163
4.500 1.1666 0.01793 0.00884 -0.1498 0.4436 0.5216
4.750 1.1902 0.01811 0.00911 -0.1493 0.4387 0.5278
5.250 1.2341 0.01856 0.00965 -0.1478 0.4284 0.5406
5.500 1.2553 0.01877 0.00996 -0.1469 0.4225 0.5482
5.750 1.2744 0.01902 0.01029 -0.1456 0.4163 0.5561
6.000 1.2934 0.01932 0.01065 -0.1444 0.4096 0.5652
6.250 1.3125 0.01965 0.01106 -0.1433 0.4009 0.5746
6.500 1.3309 0.02003 0.01151 -0.1421 0.3922 0.5851
6.750 1.3481 0.02047 0.01201 -0.1408 0.3824 0.5956
7.000 1.3641 0.02098 0.01256 -0.1394 0.3698 0.6074
7.250 1.3764 0.02167 0.01325 -0.1375 0.3529 0.6198
7.500 1.3864 0.02252 0.01408 -0.1354 0.3335 0.6329
7.750 1.3929 0.02362 0.01512 -0.1330 0.3108 0.6465
8.000 1.3962 0.02500 0.01642 -0.1304 0.2884 0.6608
8.250 1.4003 0.02643 0.01781 -0.1280 0.2719 0.6759
8.750 1.4144 0.02909 0.02056 -0.1243 0.2520 0.7111
9.000 1.4201 0.03056 0.02209 -0.1224 0.2441 0.7338
9.250 1.4269 0.03190 0.02357 -0.1207 0.2369 0.7746
9.500 1.4257 0.03318 0.02505 -0.1176 0.2303 1.0000
9.750 1.4299 0.03501 0.02688 -0.1161 0.2236 1.0000
10.000 1.4369 0.03666 0.02857 -0.1148 0.2171 1.0000
10.250 1.4402 0.03865 0.03057 -0.1133 0.2107 1.0000
10.500 1.4456 0.04054 0.03249 -0.1121 0.2052 1.0000
10.750 1.4526 0.04234 0.03434 -0.1111 0.1988 1.0000
11.000 1.4547 0.04464 0.03665 -0.1099 0.1922 1.0000
11.250 1.4624 0.04646 0.03854 -0.1090 0.1854 1.0000
11.500 1.4658 0.04874 0.04086 -0.1081 0.1747 1.0000
11.750 1.4652 0.05151 0.04360 -0.1071 0.1486 1.0000
12.000 1.4502 0.05590 0.04781 -0.1058 0.1297 1.0000
12.250 1.4459 0.05921 0.05110 -0.1049 0.1241 1.0000
12.500 1.4423 0.06254 0.05444 -0.1042 0.1194 1.0000
12.750 1.4404 0.06574 0.05768 -0.1036 0.1155 1.0000
13.000 1.4401 0.06880 0.06080 -0.1031 0.1122 1.0000
13.250 1.4395 0.07192 0.06399 -0.1027 0.1096 1.0000
13.500 1.4374 0.07527 0.06740 -0.1024 0.1070 1.0000
13.750 1.4359 0.07859 0.07079 -0.1021 0.1044 1.0000
14.000 1.4404 0.08116 0.07348 -0.1020 0.1015 1.0000
14.250 1.4408 0.08428 0.07667 -0.1018 0.0978 1.0000
14.500 1.4356 0.08812 0.08057 -0.1018 0.0940 1.0000
14.750 1.4427 0.09041 0.08296 -0.1017 0.0894 1.0000
15.000 1.4472 0.09305 0.08569 -0.1017 0.0819 1.0000
15.250 1.4310 0.09846 0.09085 -0.1021 0.0406 1.0000
15.500 1.4100 0.10462 0.09695 -0.1026 0.0249 1.0000
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