GOE 798 AIRFOIL (goe798-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 798 AIRFOIL (goe798-il) Reynolds number: 500,000 Max Cl/Cd: 98.93 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe798-il-500000.txt Download as CSV file: xf-goe798-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 798 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
------ -------- --------- --------- -------- -------- --------
-15.750 -0.6851 0.05254 0.04857 -0.1457 0.9813 0.0493
-15.500 -0.7056 0.04442 0.04015 -0.1552 0.9759 0.0495
-15.250 -0.7146 0.03940 0.03489 -0.1607 0.9683 0.0497
-15.000 -0.7200 0.03589 0.03124 -0.1626 0.9608 0.0501
-14.750 -0.7191 0.03368 0.02895 -0.1627 0.9524 0.0505
-14.500 -0.7161 0.03196 0.02716 -0.1622 0.9444 0.0508
-14.250 -0.7128 0.03050 0.02563 -0.1610 0.9358 0.0511
-14.000 -0.7079 0.02924 0.02428 -0.1596 0.9276 0.0515
-13.750 -0.7026 0.02810 0.02305 -0.1577 0.9187 0.0519
-13.500 -0.6965 0.02708 0.02192 -0.1555 0.9101 0.0524
-13.250 -0.6914 0.02622 0.02094 -0.1528 0.9006 0.0528
-13.000 -0.6804 0.02533 0.01992 -0.1510 0.8920 0.0533
-12.750 -0.6673 0.02448 0.01893 -0.1494 0.8826 0.0539
-12.500 -0.6519 0.02371 0.01800 -0.1480 0.8740 0.0544
-12.250 -0.6350 0.02303 0.01716 -0.1468 0.8640 0.0548
-12.000 -0.6193 0.02195 0.01603 -0.1455 0.8549 0.0556
-11.750 -0.6001 0.02130 0.01535 -0.1445 0.8446 0.0564
-11.500 -0.5794 0.02076 0.01474 -0.1437 0.8350 0.0571
-11.250 -0.5584 0.02023 0.01411 -0.1428 0.8249 0.0580
-11.000 -0.5368 0.01970 0.01347 -0.1421 0.8157 0.0588
-10.750 -0.5146 0.01920 0.01283 -0.1413 0.8066 0.0596
-10.500 -0.4917 0.01873 0.01221 -0.1407 0.7988 0.0603
-10.250 -0.4704 0.01806 0.01153 -0.1399 0.7910 0.0614
-10.000 -0.4469 0.01766 0.01106 -0.1394 0.7842 0.0624
-9.750 -0.4225 0.01730 0.01066 -0.1389 0.7779 0.0634
-9.500 -0.3978 0.01696 0.01024 -0.1385 0.7715 0.0647
-9.250 -0.3724 0.01667 0.00980 -0.1382 0.7657 0.0659
-9.000 -0.3482 0.01625 0.00938 -0.1377 0.7604 0.0674
-8.750 -0.3224 0.01599 0.00912 -0.1375 0.7555 0.0688
-8.500 -0.2962 0.01576 0.00883 -0.1372 0.7507 0.0705
-8.250 -0.2695 0.01554 0.00849 -0.1370 0.7463 0.0722
-8.000 -0.2431 0.01532 0.00828 -0.1369 0.7421 0.0740
-7.750 -0.2158 0.01520 0.00816 -0.1368 0.7383 0.0760
-7.500 -0.1883 0.01507 0.00796 -0.1367 0.7341 0.0785
-7.250 -0.1611 0.01494 0.00783 -0.1367 0.7301 0.0808
-7.000 -0.1327 0.01495 0.00779 -0.1367 0.7263 0.0833
-6.750 -0.1040 0.01495 0.00767 -0.1369 0.7227 0.0863
-6.500 -0.0769 0.01481 0.00760 -0.1368 0.7196 0.0887
-6.250 -0.0487 0.01481 0.00758 -0.1368 0.7163 0.0917
-6.000 -0.0206 0.01476 0.00745 -0.1369 0.7129 0.0949
-5.750 0.0071 0.01467 0.00738 -0.1369 0.7095 0.0975
-5.500 0.0358 0.01470 0.00735 -0.1370 0.7062 0.1006
-5.250 0.0648 0.01481 0.00734 -0.1373 0.7029 0.1032
-5.000 0.0915 0.01445 0.00706 -0.1372 0.7004 0.1060
-4.750 0.1193 0.01438 0.00701 -0.1372 0.6974 0.1086
-4.500 0.1474 0.01434 0.00692 -0.1373 0.6940 0.1112
-4.250 0.1754 0.01423 0.00675 -0.1373 0.6905 0.1134
-4.000 0.2028 0.01393 0.00646 -0.1373 0.6868 0.1159
-3.750 0.2315 0.01388 0.00638 -0.1375 0.6830 0.1181
-3.500 0.2587 0.01376 0.00627 -0.1374 0.6799 0.1203
-3.250 0.2864 0.01367 0.00617 -0.1374 0.6764 0.1223
-3.000 0.3144 0.01358 0.00605 -0.1374 0.6731 0.1238
-2.750 0.3413 0.01325 0.00573 -0.1373 0.6698 0.1261
-2.500 0.3695 0.01313 0.00559 -0.1374 0.6663 0.1281
-2.250 0.3978 0.01308 0.00553 -0.1376 0.6627 0.1302
-2.000 0.4247 0.01297 0.00544 -0.1374 0.6594 0.1324
-1.750 0.4522 0.01291 0.00537 -0.1373 0.6558 0.1346
-1.500 0.4792 0.01272 0.00519 -0.1372 0.6520 0.1372
-1.250 0.5065 0.01257 0.00504 -0.1371 0.6484 0.1394
-1.000 0.5352 0.01253 0.00496 -0.1373 0.6448 0.1412
-0.750 0.5622 0.01245 0.00492 -0.1372 0.6418 0.1430
-0.500 0.5889 0.01237 0.00486 -0.1370 0.6384 0.1452
-0.250 0.6160 0.01231 0.00480 -0.1369 0.6347 0.1473
0.000 0.6431 0.01222 0.00471 -0.1367 0.6312 0.1500
0.250 0.6708 0.01215 0.00465 -0.1368 0.6278 0.1540
0.500 0.6995 0.01215 0.00465 -0.1370 0.6243 0.1590
0.750 0.7251 0.01207 0.00465 -0.1366 0.6211 0.1665
1.000 0.7510 0.01198 0.00465 -0.1363 0.6173 0.1832
1.250 0.7767 0.01181 0.00466 -0.1360 0.6135 0.2317
1.500 0.8024 0.01160 0.00468 -0.1358 0.6097 0.3062
1.750 0.8286 0.01135 0.00473 -0.1358 0.6057 0.4211
2.000 0.8484 0.01085 0.00485 -0.1344 0.6020 0.6077
2.250 0.8655 0.01036 0.00500 -0.1321 0.5977 0.8001
2.500 0.9020 0.01034 0.00527 -0.1333 0.5929 0.9498
2.750 0.9448 0.01053 0.00537 -0.1365 0.5877 0.9795
3.000 0.9968 0.01071 0.00555 -0.1418 0.5821 0.9930
3.250 1.0489 0.01086 0.00567 -0.1473 0.5757 1.0000
3.500 1.0662 0.01095 0.00569 -0.1452 0.5702 1.0000
3.750 1.0824 0.01104 0.00576 -0.1429 0.5646 1.0000
4.000 1.0971 0.01112 0.00584 -0.1404 0.5580 1.0000
4.250 1.1106 0.01124 0.00589 -0.1375 0.5515 1.0000
4.500 1.1228 0.01135 0.00600 -0.1344 0.5445 1.0000
4.750 1.1289 0.01147 0.00609 -0.1300 0.5366 1.0000
5.000 1.1384 0.01165 0.00623 -0.1265 0.5286 1.0000
5.250 1.1496 0.01186 0.00642 -0.1233 0.5185 1.0000
5.500 1.1617 0.01215 0.00666 -0.1204 0.5074 1.0000
5.750 1.1721 0.01254 0.00697 -0.1174 0.4944 1.0000
6.000 1.1828 0.01300 0.00736 -0.1145 0.4794 1.0000
6.250 1.1930 0.01355 0.00783 -0.1116 0.4634 1.0000
6.500 1.2026 0.01419 0.00839 -0.1088 0.4471 1.0000
6.750 1.2116 0.01492 0.00903 -0.1059 0.4315 1.0000
7.000 1.2210 0.01570 0.00972 -0.1033 0.4177 1.0000
7.500 1.2444 0.01721 0.01113 -0.0991 0.3967 1.0000
7.750 1.2550 0.01807 0.01191 -0.0969 0.3884 1.0000
8.000 1.2709 0.01872 0.01256 -0.0955 0.3819 1.0000
8.250 1.2849 0.01947 0.01328 -0.0940 0.3757 1.0000
8.500 1.2963 0.02038 0.01413 -0.0921 0.3699 1.0000
8.750 1.3139 0.02099 0.01476 -0.0911 0.3656 1.0000
9.000 1.3301 0.02168 0.01546 -0.0900 0.3612 1.0000
9.250 1.3443 0.02250 0.01626 -0.0887 0.3572 1.0000
9.500 1.3575 0.02338 0.01710 -0.0872 0.3530 1.0000
9.750 1.3745 0.02408 0.01782 -0.0863 0.3497 1.0000
10.000 1.3912 0.02481 0.01859 -0.0854 0.3464 1.0000
10.250 1.4069 0.02560 0.01940 -0.0844 0.3428 1.0000
10.500 1.4212 0.02649 0.02027 -0.0833 0.3392 1.0000
10.750 1.4351 0.02740 0.02116 -0.0822 0.3357 1.0000
11.000 1.4518 0.02815 0.02191 -0.0813 0.3329 1.0000
11.250 1.4680 0.02898 0.02280 -0.0806 0.3303 1.0000
11.500 1.4834 0.02987 0.02374 -0.0798 0.3273 1.0000
11.750 1.4984 0.03077 0.02466 -0.0789 0.3243 1.0000
12.000 1.5123 0.03175 0.02564 -0.0780 0.3212 1.0000
12.250 1.5266 0.03267 0.02654 -0.0770 0.3179 1.0000
12.500 1.5426 0.03350 0.02740 -0.0763 0.3152 1.0000
12.750 1.5570 0.03452 0.02850 -0.0756 0.3128 1.0000
13.000 1.5705 0.03563 0.02966 -0.0749 0.3098 1.0000
13.250 1.5836 0.03674 0.03081 -0.0741 0.3066 1.0000
13.500 1.5956 0.03792 0.03200 -0.0732 0.3032 1.0000
13.750 1.6087 0.03893 0.03298 -0.0723 0.2994 1.0000
14.000 1.6209 0.04018 0.03431 -0.0716 0.2967 1.0000
14.250 1.6324 0.04153 0.03574 -0.0709 0.2935 1.0000
14.500 1.6426 0.04297 0.03724 -0.0702 0.2897 1.0000
14.750 1.6520 0.04444 0.03871 -0.0693 0.2856 1.0000
15.000 1.6608 0.04593 0.04020 -0.0684 0.2813 1.0000
15.250 1.6702 0.04754 0.04193 -0.0678 0.2774 1.0000
15.500 1.6781 0.04926 0.04370 -0.0671 0.2724 1.0000
15.750 1.6822 0.05128 0.04571 -0.0661 0.2671 1.0000
16.000 1.6898 0.05308 0.04759 -0.0654 0.2615 1.0000
16.250 1.6933 0.05530 0.04985 -0.0647 0.2546 1.0000
16.500 1.6948 0.05770 0.05226 -0.0638 0.2470 1.0000
16.750 1.6935 0.06042 0.05500 -0.0629 0.2371 1.0000
17.000 1.6912 0.06327 0.05786 -0.0620 0.2263 1.0000
17.250 1.6854 0.06648 0.06104 -0.0610 0.2151 1.0000
17.500 1.6753 0.07019 0.06471 -0.0599 0.2047 1.0000
17.750 1.6700 0.07342 0.06793 -0.0591 0.1960 1.0000
18.000 1.6633 0.07678 0.07128 -0.0583 0.1892 1.0000
18.250 1.6589 0.07995 0.07447 -0.0577 0.1836 1.0000
18.500 1.6522 0.08338 0.07788 -0.0571 0.1785 1.0000
18.750 1.6529 0.08606 0.08062 -0.0568 0.1750 1.0000
19.000 1.6521 0.08891 0.08350 -0.0565 0.1713 1.0000
19.250 1.6475 0.09216 0.08676 -0.0562 0.1676 1.0000
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