GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il) Reynolds number: 500,000 Max Cl/Cd: 95.51 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe223-il-500000.txt Download as CSV file: xf-goe223-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.0764 0.10112 0.09859 -0.0878 0.8687 0.0354
-12.250 -0.4200 0.05671 0.05350 -0.1172 0.8947 0.0277
-12.000 -0.4213 0.05332 0.05003 -0.1194 0.8868 0.0279
-11.750 -0.4256 0.04971 0.04629 -0.1223 0.8789 0.0280
-11.500 -0.4286 0.04622 0.04266 -0.1255 0.8711 0.0282
-11.250 -0.3966 0.04796 0.04453 -0.1248 0.8651 0.0310
-11.000 -0.4085 0.04302 0.03935 -0.1294 0.8572 0.0303
-10.750 -0.4158 0.03744 0.03337 -0.1369 0.8489 0.0294
-10.500 -0.4099 0.03342 0.02890 -0.1400 0.8429 0.0289
-10.250 -0.3935 0.03101 0.02626 -0.1416 0.8368 0.0291
-10.000 -0.3739 0.02909 0.02411 -0.1427 0.8313 0.0295
-9.750 -0.3524 0.02742 0.02221 -0.1436 0.8269 0.0299
-9.500 -0.3290 0.02607 0.02067 -0.1445 0.8223 0.0306
-9.250 -0.3042 0.02501 0.01942 -0.1452 0.8175 0.0314
-9.000 -0.2782 0.02430 0.01847 -0.1459 0.8131 0.0319
-8.750 -0.2530 0.02304 0.01698 -0.1464 0.8089 0.0324
-8.500 -0.2290 0.02115 0.01509 -0.1463 0.8042 0.0329
-8.250 -0.2037 0.02003 0.01398 -0.1464 0.7993 0.0335
-8.000 -0.1775 0.01927 0.01319 -0.1466 0.7947 0.0343
-7.750 -0.1508 0.01858 0.01247 -0.1468 0.7899 0.0351
-7.500 -0.1240 0.01788 0.01173 -0.1470 0.7847 0.0357
-7.250 -0.0969 0.01723 0.01102 -0.1472 0.7798 0.0362
-7.000 -0.0695 0.01665 0.01037 -0.1475 0.7750 0.0368
-6.750 -0.0417 0.01612 0.00981 -0.1478 0.7694 0.0374
-6.500 -0.0133 0.01574 0.00935 -0.1482 0.7637 0.0380
-6.250 0.0140 0.01503 0.00858 -0.1486 0.7583 0.0385
-6.000 0.0417 0.01426 0.00782 -0.1493 0.7516 0.0392
-5.750 0.0703 0.01368 0.00718 -0.1499 0.7449 0.0399
-5.500 0.0994 0.01318 0.00665 -0.1506 0.7376 0.0407
-5.250 0.1285 0.01276 0.00617 -0.1512 0.7297 0.0417
-5.000 0.1578 0.01240 0.00575 -0.1518 0.7215 0.0429
-4.750 0.1870 0.01208 0.00534 -0.1523 0.7121 0.0439
-4.500 0.2161 0.01181 0.00499 -0.1528 0.7009 0.0447
-4.250 0.2450 0.01153 0.00462 -0.1532 0.6878 0.0458
-4.000 0.2736 0.01130 0.00429 -0.1535 0.6721 0.0479
-3.750 0.3018 0.01116 0.00403 -0.1537 0.6533 0.0504
-3.500 0.3296 0.01105 0.00381 -0.1538 0.6330 0.0568
-3.250 0.3575 0.01060 0.00349 -0.1544 0.6138 0.1281
-3.000 0.3856 0.00976 0.00321 -0.1556 0.5976 0.3261
-2.750 0.4135 0.00987 0.00327 -0.1556 0.5843 0.3512
-2.500 0.4412 0.01003 0.00335 -0.1556 0.5725 0.3676
-2.250 0.4687 0.01023 0.00342 -0.1556 0.5618 0.3786
-2.000 0.4965 0.01037 0.00353 -0.1556 0.5526 0.3886
-1.750 0.5243 0.01056 0.00360 -0.1557 0.5453 0.3969
-1.500 0.5526 0.01067 0.00371 -0.1558 0.5390 0.4046
-1.250 0.5805 0.01084 0.00378 -0.1559 0.5334 0.4100
-1.000 0.6087 0.01094 0.00383 -0.1560 0.5286 0.4147
-0.750 0.6370 0.01102 0.00393 -0.1562 0.5236 0.4205
-0.500 0.6649 0.01119 0.00404 -0.1562 0.5186 0.4274
-0.250 0.6925 0.01134 0.00412 -0.1563 0.5144 0.4329
0.000 0.7208 0.01142 0.00423 -0.1565 0.5110 0.4384
0.250 0.7492 0.01151 0.00432 -0.1566 0.5074 0.4435
0.500 0.7772 0.01162 0.00438 -0.1568 0.5035 0.4469
0.750 0.8048 0.01169 0.00443 -0.1569 0.4997 0.4503
1.000 0.8323 0.01181 0.00453 -0.1570 0.4960 0.4537
1.250 0.8605 0.01186 0.00461 -0.1571 0.4929 0.4573
1.500 0.8884 0.01192 0.00468 -0.1573 0.4892 0.4608
1.750 0.9159 0.01203 0.00475 -0.1573 0.4852 0.4640
2.000 0.9430 0.01213 0.00484 -0.1574 0.4817 0.4675
2.250 0.9703 0.01224 0.00496 -0.1574 0.4785 0.4714
2.500 0.9979 0.01229 0.00506 -0.1575 0.4753 0.4756
2.750 1.0251 0.01238 0.00515 -0.1576 0.4714 0.4798
3.000 1.0514 0.01249 0.00525 -0.1574 0.4667 0.4836
3.250 1.0774 0.01263 0.00539 -0.1573 0.4626 0.4878
3.500 1.1044 0.01267 0.00550 -0.1573 0.4585 0.4924
3.750 1.1308 0.01277 0.00562 -0.1572 0.4540 0.4974
4.000 1.1564 0.01289 0.00575 -0.1570 0.4498 0.5025
4.250 1.1815 0.01304 0.00592 -0.1567 0.4457 0.5079
4.500 1.2078 0.01312 0.00606 -0.1566 0.4413 0.5138
4.750 1.2328 0.01324 0.00621 -0.1563 0.4358 0.5195
5.000 1.2558 0.01342 0.00640 -0.1557 0.4299 0.5257
5.250 1.2811 0.01352 0.00657 -0.1554 0.4239 0.5330
5.500 1.3035 0.01369 0.00677 -0.1547 0.4170 0.5402
5.750 1.3247 0.01387 0.00699 -0.1536 0.4097 0.5489
6.000 1.3438 0.01411 0.00725 -0.1523 0.3998 0.5576
6.250 1.3650 0.01437 0.00754 -0.1515 0.3891 0.5678
6.500 1.3840 0.01473 0.00792 -0.1503 0.3759 0.5783
6.750 1.4003 0.01524 0.00839 -0.1487 0.3573 0.5901
7.000 1.4088 0.01616 0.00916 -0.1461 0.3246 0.6025
7.250 1.4084 0.01764 0.01041 -0.1424 0.2794 0.6145
7.500 1.4121 0.01899 0.01164 -0.1394 0.2522 0.6282
7.750 1.4210 0.02009 0.01270 -0.1373 0.2372 0.6441
8.000 1.4321 0.02108 0.01369 -0.1355 0.2271 0.6611
8.250 1.4448 0.02200 0.01464 -0.1340 0.2192 0.6792
8.500 1.4578 0.02293 0.01562 -0.1326 0.2130 0.6983
8.750 1.4720 0.02378 0.01655 -0.1314 0.2068 0.7201
9.000 1.4833 0.02481 0.01767 -0.1299 0.2008 0.7494
9.250 1.4930 0.02527 0.01852 -0.1277 0.1961 1.0000
9.500 1.5050 0.02641 0.01965 -0.1265 0.1881 1.0000
9.750 1.5158 0.02764 0.02087 -0.1252 0.1792 1.0000
10.000 1.5202 0.02940 0.02252 -0.1234 0.1555 1.0000
10.250 1.5121 0.03217 0.02510 -0.1207 0.1288 1.0000
10.500 1.5136 0.03427 0.02719 -0.1189 0.1220 1.0000
10.750 1.5194 0.03609 0.02904 -0.1176 0.1185 1.0000
11.000 1.5245 0.03802 0.03101 -0.1163 0.1160 1.0000
11.250 1.5278 0.04015 0.03318 -0.1150 0.1136 1.0000
11.500 1.5294 0.04253 0.03559 -0.1137 0.1108 1.0000
11.750 1.5298 0.04509 0.03820 -0.1125 0.1075 1.0000
12.000 1.5379 0.04693 0.04013 -0.1117 0.1056 1.0000
12.250 1.5417 0.04923 0.04250 -0.1108 0.1029 1.0000
12.500 1.5412 0.05205 0.04536 -0.1098 0.0998 1.0000
12.750 1.5377 0.05527 0.04862 -0.1089 0.0964 1.0000
13.000 1.5493 0.05687 0.05029 -0.1085 0.0917 1.0000
13.250 1.5506 0.05962 0.05304 -0.1078 0.0853 1.0000
13.500 1.5447 0.06321 0.05648 -0.1071 0.0559 1.0000
13.750 1.5163 0.06959 0.06275 -0.1060 0.0311 1.0000
14.000 1.5038 0.07418 0.06737 -0.1054 0.0229 1.0000
14.250 1.5001 0.07776 0.07100 -0.1051 0.0205 1.0000
14.500 1.4986 0.08111 0.07443 -0.1048 0.0193 1.0000
14.750 1.4959 0.08463 0.07804 -0.1046 0.0183 1.0000
15.000 1.4922 0.08830 0.08179 -0.1045 0.0175 1.0000
15.250 1.4909 0.09166 0.08524 -0.1044 0.0171 1.0000
15.500 1.4889 0.09517 0.08884 -0.1044 0.0167 1.0000
15.750 1.4868 0.09869 0.09244 -0.1045 0.0163 1.0000
16.000 1.4831 0.10249 0.09634 -0.1047 0.0159 1.0000
16.250 1.4795 0.10629 0.10022 -0.1049 0.0156 1.0000
16.500 1.4741 0.11036 0.10439 -0.1053 0.0153 1.0000
16.750 1.4678 0.11461 0.10873 -0.1059 0.0150 1.0000
17.000 1.4602 0.11913 0.11333 -0.1066 0.0147 1.0000
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