GOE 798 AIRFOIL (goe798-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 798 AIRFOIL (goe798-il) Reynolds number: 200,000 Max Cl/Cd: 65.67 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe798-il-200000.txt Download as CSV file: xf-goe798-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 0.0470 0.09721 0.09286 -0.1258 0.8806 0.1042
-10.000 0.0618 0.09524 0.09086 -0.1252 0.8733 0.1052
-9.750 -0.1074 0.05966 0.05511 -0.1512 0.8621 0.0865
-9.500 -0.1824 0.04969 0.04479 -0.1540 0.8498 0.0854
-9.250 -0.2525 0.04040 0.03464 -0.1510 0.8414 0.0857
-9.000 -0.2630 0.03690 0.03070 -0.1483 0.8339 0.0867
-8.750 -0.2368 0.03667 0.03057 -0.1481 0.8284 0.0876
-8.500 -0.2120 0.03613 0.03001 -0.1480 0.8240 0.0888
-8.250 -0.1957 0.03475 0.02844 -0.1472 0.8197 0.0904
-8.000 -0.1913 0.03266 0.02596 -0.1449 0.8131 0.0926
-7.750 -0.1810 0.03057 0.02339 -0.1432 0.8082 0.0948
-7.500 -0.1532 0.03005 0.02292 -0.1435 0.8047 0.0964
-7.250 -0.1268 0.02941 0.02220 -0.1435 0.8015 0.0983
-7.000 -0.1115 0.02856 0.02117 -0.1419 0.7956 0.1007
-6.750 -0.0936 0.02737 0.01961 -0.1407 0.7907 0.1038
-6.500 -0.0659 0.02685 0.01916 -0.1409 0.7871 0.1060
-6.250 -0.0382 0.02630 0.01850 -0.1411 0.7841 0.1091
-6.000 -0.0172 0.02575 0.01756 -0.1400 0.7804 0.1128
-5.750 0.0044 0.02503 0.01698 -0.1394 0.7756 0.1155
-5.500 0.0296 0.02472 0.01667 -0.1391 0.7714 0.1191
-5.250 0.0556 0.02425 0.01588 -0.1388 0.7679 0.1238
-5.000 0.0850 0.02349 0.01519 -0.1393 0.7651 0.1275
-4.750 0.1124 0.02326 0.01489 -0.1394 0.7621 0.1319
-4.500 0.1321 0.02311 0.01460 -0.1381 0.7575 0.1360
-4.250 0.1564 0.02270 0.01431 -0.1377 0.7534 0.1397
-4.000 0.1836 0.02247 0.01402 -0.1377 0.7498 0.1439
-3.750 0.2133 0.02227 0.01364 -0.1380 0.7469 0.1480
-3.500 0.2438 0.02171 0.01309 -0.1387 0.7444 0.1519
-3.250 0.2671 0.02172 0.01314 -0.1380 0.7408 0.1554
-3.000 0.2881 0.02174 0.01315 -0.1369 0.7360 0.1589
-2.750 0.3143 0.02165 0.01296 -0.1366 0.7318 0.1621
-2.500 0.3440 0.02113 0.01246 -0.1370 0.7282 0.1661
-2.250 0.3772 0.02085 0.01215 -0.1379 0.7249 0.1707
-2.000 0.4002 0.02087 0.01216 -0.1370 0.7200 0.1745
-1.750 0.4222 0.02086 0.01212 -0.1360 0.7145 0.1772
-1.500 0.4500 0.02047 0.01175 -0.1359 0.7102 0.1804
-1.250 0.4822 0.02010 0.01137 -0.1366 0.7065 0.1838
-1.000 0.5144 0.01991 0.01114 -0.1374 0.7028 0.1879
-0.750 0.5311 0.01999 0.01128 -0.1354 0.6967 0.1917
-0.500 0.5564 0.01985 0.01115 -0.1349 0.6919 0.1959
-0.250 0.5854 0.01958 0.01093 -0.1351 0.6883 0.2019
0.000 0.6184 0.01937 0.01069 -0.1359 0.6852 0.2102
0.250 0.6429 0.01934 0.01076 -0.1355 0.6814 0.2211
0.500 0.6601 0.01940 0.01099 -0.1336 0.6762 0.2380
0.750 0.6837 0.01915 0.01099 -0.1330 0.6718 0.2853
1.000 0.7083 0.01843 0.01090 -0.1326 0.6683 0.4454
1.250 0.7292 0.01737 0.01097 -0.1305 0.6653 0.7865
1.500 0.8059 0.01754 0.01133 -0.1395 0.6607 0.9708
1.750 0.8770 0.01772 0.01145 -0.1487 0.6547 0.9990
2.000 0.9025 0.01770 0.01134 -0.1483 0.6500 1.0000
2.250 0.9318 0.01760 0.01110 -0.1485 0.6462 1.0000
2.500 0.9515 0.01774 0.01118 -0.1471 0.6416 1.0000
2.750 0.9608 0.01797 0.01143 -0.1436 0.6354 1.0000
3.000 0.9835 0.01795 0.01133 -0.1426 0.6305 1.0000
3.250 1.0151 0.01781 0.01106 -0.1432 0.6264 1.0000
3.500 1.0278 0.01802 0.01128 -0.1404 0.6205 1.0000
3.750 1.0411 0.01814 0.01139 -0.1376 0.6140 1.0000
4.000 1.0693 0.01801 0.01116 -0.1376 0.6089 1.0000
4.250 1.0915 0.01803 0.01112 -0.1365 0.6033 1.0000
4.500 1.0991 0.01820 0.01132 -0.1326 0.5956 1.0000
4.750 1.1265 0.01805 0.01107 -0.1324 0.5895 1.0000
5.000 1.1392 0.01819 0.01120 -0.1296 0.5820 1.0000
5.250 1.1532 0.01824 0.01123 -0.1269 0.5739 1.0000
5.500 1.1801 0.01818 0.01105 -0.1267 0.5670 1.0000
5.750 1.1792 0.01845 0.01138 -0.1213 0.5572 1.0000
6.000 1.2071 0.01838 0.01116 -0.1212 0.5495 1.0000
6.250 1.2004 0.01879 0.01164 -0.1149 0.5384 1.0000
6.500 1.2198 0.01891 0.01166 -0.1134 0.5291 1.0000
6.750 1.2264 0.01931 0.01204 -0.1098 0.5178 1.0000
7.000 1.2383 0.01971 0.01239 -0.1072 0.5070 1.0000
7.250 1.2565 0.02000 0.01256 -0.1057 0.4968 1.0000
7.500 1.2634 0.02065 0.01320 -0.1026 0.4855 1.0000
7.750 1.2829 0.02101 0.01342 -0.1014 0.4760 1.0000
8.000 1.2906 0.02173 0.01414 -0.0986 0.4654 1.0000
8.250 1.3082 0.02223 0.01453 -0.0973 0.4567 1.0000
8.500 1.3189 0.02296 0.01526 -0.0951 0.4482 1.0000
8.750 1.3445 0.02330 0.01543 -0.0950 0.4415 1.0000
9.000 1.3529 0.02418 0.01639 -0.0926 0.4347 1.0000
9.250 1.3696 0.02480 0.01697 -0.0914 0.4285 1.0000
9.500 1.3957 0.02516 0.01721 -0.0915 0.4229 1.0000
9.750 1.4036 0.02611 0.01825 -0.0892 0.4171 1.0000
10.000 1.4186 0.02682 0.01896 -0.0879 0.4117 1.0000
10.250 1.4458 0.02714 0.01915 -0.0881 0.4067 1.0000
10.500 1.4572 0.02804 0.02012 -0.0864 0.4019 1.0000
10.750 1.4684 0.02894 0.02108 -0.0848 0.3971 1.0000
11.000 1.4852 0.02962 0.02175 -0.0838 0.3925 1.0000
11.250 1.5170 0.02980 0.02180 -0.0846 0.3881 1.0000
11.500 1.5227 0.03096 0.02310 -0.0824 0.3840 1.0000
11.750 1.5319 0.03201 0.02422 -0.0807 0.3797 1.0000
12.000 1.5470 0.03280 0.02503 -0.0796 0.3756 1.0000
12.250 1.5724 0.03317 0.02535 -0.0798 0.3718 1.0000
12.500 1.5915 0.03390 0.02610 -0.0792 0.3680 1.0000
12.750 1.5925 0.03536 0.02770 -0.0768 0.3639 1.0000
13.000 1.6014 0.03648 0.02888 -0.0752 0.3595 1.0000
13.250 1.6191 0.03715 0.02954 -0.0746 0.3553 1.0000
13.500 1.6478 0.03741 0.02973 -0.0750 0.3510 1.0000
13.750 1.6398 0.03942 0.03193 -0.0720 0.3470 1.0000
14.000 1.6433 0.04091 0.03352 -0.0702 0.3424 1.0000
14.250 1.6578 0.04175 0.03436 -0.0693 0.3379 1.0000
14.500 1.6851 0.04197 0.03449 -0.0696 0.3332 1.0000
14.750 1.6689 0.04471 0.03746 -0.0663 0.3284 1.0000
15.000 1.6701 0.04647 0.03930 -0.0646 0.3232 1.0000
15.250 1.6891 0.04700 0.03978 -0.0642 0.3183 1.0000
15.500 1.6887 0.04901 0.04189 -0.0626 0.3131 1.0000
15.750 1.6781 0.05182 0.04484 -0.0604 0.3072 1.0000
16.000 1.6893 0.05290 0.04589 -0.0596 0.3016 1.0000
16.250 1.6878 0.05515 0.04822 -0.0582 0.2956 1.0000
16.500 1.6757 0.05839 0.05160 -0.0565 0.2888 1.0000
16.750 1.6924 0.05901 0.05212 -0.0561 0.2829 1.0000
17.000 1.6705 0.06342 0.05675 -0.0542 0.2756 1.0000
17.250 1.6695 0.06586 0.05922 -0.0534 0.2689 1.0000
17.500 1.6690 0.06832 0.06170 -0.0525 0.2624 1.0000
17.750 1.6569 0.07215 0.06565 -0.0516 0.2552 1.0000
18.000 1.6736 0.07274 0.06610 -0.0513 0.2496 1.0000
18.250 1.6501 0.07807 0.07167 -0.0505 0.2425 1.0000
18.500 1.6534 0.08029 0.07387 -0.0502 0.2368 1.0000
18.750 1.6515 0.08316 0.07678 -0.0498 0.2313 1.0000
19.000 1.6425 0.08700 0.08073 -0.0495 0.2256 1.0000
19.250 1.6536 0.08827 0.08192 -0.0494 0.2209 1.0000
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