GOE 535 AIRFOIL (goe535-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 535 AIRFOIL (goe535-il) Reynolds number: 200,000 Max Cl/Cd: 68.07 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe535-il-200000.txt Download as CSV file: xf-goe535-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 535 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.2152 0.12486 0.12108 -0.0363 1.0000 0.0761
-11.000 -0.2160 0.12287 0.11914 -0.0355 1.0000 0.0777
-10.500 -0.2652 0.11767 0.11409 -0.0377 1.0000 0.0809
-10.250 -0.2591 0.11605 0.11252 -0.0347 1.0000 0.0812
-10.000 -0.2267 0.11269 0.10915 -0.0369 0.9974 0.0820
-9.750 -0.1994 0.10920 0.10565 -0.0405 0.9939 0.0835
-9.500 -0.1790 0.10525 0.10170 -0.0455 0.9895 0.0861
-9.250 -0.1809 0.09839 0.09484 -0.0560 0.9827 0.0897
-9.000 -0.0243 0.08524 0.08182 -0.0712 0.9574 0.0961
-8.750 -0.0301 0.07804 0.07462 -0.0790 0.9523 0.0992
-8.500 0.0003 0.07528 0.07186 -0.0799 0.9461 0.1005
-8.250 -0.2017 0.05602 0.05224 -0.1053 0.9391 0.0810
-8.000 -0.1679 0.05328 0.04951 -0.1086 0.9353 0.0816
-7.750 -0.1758 0.03624 0.03148 -0.1332 0.9172 0.0768
-7.500 -0.1574 0.03186 0.02657 -0.1366 0.9038 0.0775
-7.250 -0.1258 0.02837 0.02252 -0.1403 0.8960 0.0791
-7.000 -0.1017 0.02608 0.01967 -0.1412 0.8826 0.0810
-6.750 -0.0710 0.02492 0.01862 -0.1418 0.8717 0.0830
-6.500 -0.0387 0.02386 0.01742 -0.1427 0.8605 0.0856
-6.250 -0.0128 0.02268 0.01588 -0.1426 0.8456 0.0882
-6.000 0.0153 0.02133 0.01432 -0.1428 0.8324 0.0904
-5.750 0.0452 0.02060 0.01356 -0.1429 0.8195 0.0932
-5.500 0.0711 0.02000 0.01277 -0.1424 0.8043 0.0964
-5.250 0.0979 0.01917 0.01171 -0.1420 0.7903 0.0994
-5.000 0.1260 0.01853 0.01102 -0.1418 0.7770 0.1024
-4.750 0.1515 0.01811 0.01048 -0.1410 0.7619 0.1059
-4.500 0.1780 0.01772 0.00987 -0.1404 0.7480 0.1090
-4.250 0.2050 0.01708 0.00922 -0.1400 0.7358 0.1126
-4.000 0.2300 0.01676 0.00885 -0.1392 0.7214 0.1163
-3.750 0.2567 0.01654 0.00846 -0.1385 0.7083 0.1197
-3.500 0.2824 0.01601 0.00791 -0.1378 0.6955 0.1236
-3.250 0.3075 0.01574 0.00764 -0.1370 0.6819 0.1277
-3.000 0.3344 0.01559 0.00734 -0.1364 0.6701 0.1319
-2.750 0.3591 0.01522 0.00700 -0.1356 0.6571 0.1365
-2.500 0.3850 0.01505 0.00680 -0.1349 0.6449 0.1417
-2.250 0.4111 0.01488 0.00655 -0.1341 0.6331 0.1477
-2.000 0.4363 0.01468 0.00639 -0.1334 0.6211 0.1557
-1.750 0.4629 0.01454 0.00619 -0.1329 0.6108 0.1664
-1.500 0.4880 0.01432 0.00607 -0.1321 0.5993 0.1870
-1.250 0.5130 0.01380 0.00601 -0.1317 0.5898 0.3119
-1.000 0.5382 0.01402 0.00637 -0.1307 0.5791 0.3964
-0.750 0.5650 0.01433 0.00657 -0.1300 0.5702 0.4252
-0.500 0.5908 0.01459 0.00682 -0.1291 0.5609 0.4434
-0.250 0.6171 0.01481 0.00696 -0.1284 0.5522 0.4580
0.000 0.6437 0.01509 0.00716 -0.1277 0.5443 0.4714
0.250 0.6693 0.01527 0.00735 -0.1269 0.5360 0.4820
0.500 0.6966 0.01556 0.00749 -0.1264 0.5291 0.4946
0.750 0.7218 0.01576 0.00776 -0.1255 0.5216 0.5051
1.000 0.7480 0.01598 0.00790 -0.1249 0.5144 0.5167
1.250 0.7751 0.01621 0.00807 -0.1244 0.5083 0.5254
1.500 0.8004 0.01643 0.00828 -0.1236 0.5016 0.5365
1.750 0.8254 0.01657 0.00847 -0.1227 0.4949 0.5469
2.000 0.8527 0.01683 0.00860 -0.1224 0.4891 0.5588
2.250 0.8776 0.01697 0.00881 -0.1216 0.4831 0.5665
2.500 0.9033 0.01709 0.00890 -0.1210 0.4766 0.5728
2.750 0.9303 0.01723 0.00894 -0.1207 0.4709 0.5785
3.000 0.9565 0.01740 0.00910 -0.1202 0.4651 0.5839
3.250 0.9810 0.01750 0.00923 -0.1194 0.4585 0.5896
3.500 1.0072 0.01766 0.00930 -0.1190 0.4525 0.5958
3.750 1.0344 0.01786 0.00945 -0.1188 0.4469 0.6013
4.000 1.0575 0.01797 0.00965 -0.1178 0.4409 0.6084
4.250 1.0828 0.01812 0.00978 -0.1172 0.4351 0.6161
4.500 1.1099 0.01831 0.00992 -0.1169 0.4300 0.6234
4.750 1.1344 0.01855 0.01020 -0.1163 0.4246 0.6319
5.000 1.1580 0.01866 0.01040 -0.1154 0.4188 0.6402
5.250 1.1832 0.01882 0.01055 -0.1149 0.4134 0.6506
5.500 1.2103 0.01911 0.01079 -0.1147 0.4083 0.6620
5.750 1.2319 0.01925 0.01110 -0.1136 0.4027 0.6758
6.000 1.2575 0.01940 0.01134 -0.1131 0.3971 0.6936
6.250 1.2857 0.01955 0.01154 -0.1132 0.3919 0.7210
6.500 1.3215 0.01952 0.01194 -0.1150 0.3857 1.0000
6.750 1.3439 0.01981 0.01223 -0.1141 0.3797 1.0000
7.000 1.3683 0.02010 0.01243 -0.1135 0.3743 1.0000
7.250 1.3928 0.02054 0.01280 -0.1130 0.3689 1.0000
7.500 1.4116 0.02086 0.01320 -0.1114 0.3630 1.0000
7.750 1.4332 0.02116 0.01347 -0.1103 0.3575 1.0000
8.000 1.4596 0.02161 0.01377 -0.1101 0.3523 1.0000
8.250 1.4741 0.02197 0.01428 -0.1079 0.3464 1.0000
8.500 1.4926 0.02229 0.01461 -0.1063 0.3405 1.0000
8.750 1.5162 0.02269 0.01487 -0.1056 0.3352 1.0000
9.000 1.5287 0.02312 0.01543 -0.1031 0.3291 1.0000
9.250 1.5431 0.02347 0.01580 -0.1009 0.3231 1.0000
9.500 1.5639 0.02387 0.01608 -0.0998 0.3175 1.0000
9.750 1.5709 0.02437 0.01670 -0.0964 0.3118 1.0000
10.000 1.5809 0.02480 0.01717 -0.0936 0.3059 1.0000
10.250 1.5994 0.02528 0.01753 -0.0923 0.3005 1.0000
10.500 1.6063 0.02592 0.01829 -0.0893 0.2950 1.0000
10.750 1.6152 0.02652 0.01895 -0.0867 0.2894 1.0000
11.000 1.6306 0.02709 0.01943 -0.0851 0.2843 1.0000
11.250 1.6389 0.02790 0.02033 -0.0827 0.2792 1.0000
11.500 1.6462 0.02872 0.02123 -0.0803 0.2741 1.0000
11.750 1.6580 0.02947 0.02195 -0.0785 0.2695 1.0000
12.000 1.6701 0.03033 0.02281 -0.0769 0.2647 1.0000
12.250 1.6729 0.03145 0.02407 -0.0744 0.2597 1.0000
12.500 1.6799 0.03247 0.02512 -0.0724 0.2550 1.0000
12.750 1.6972 0.03324 0.02575 -0.0715 0.2504 1.0000
13.000 1.6963 0.03476 0.02747 -0.0692 0.2464 1.0000
13.250 1.7006 0.03615 0.02896 -0.0674 0.2422 1.0000
13.500 1.7080 0.03739 0.03022 -0.0660 0.2383 1.0000
13.750 1.7220 0.03839 0.03114 -0.0650 0.2342 1.0000
14.000 1.7194 0.04038 0.03332 -0.0633 0.2306 1.0000
14.250 1.7205 0.04222 0.03527 -0.0620 0.2265 1.0000
14.500 1.7257 0.04380 0.03688 -0.0609 0.2227 1.0000
14.750 1.7376 0.04499 0.03800 -0.0600 0.2188 1.0000
15.000 1.7306 0.04769 0.04091 -0.0589 0.2153 1.0000
15.250 1.7285 0.05009 0.04343 -0.0581 0.2114 1.0000
15.500 1.7316 0.05207 0.04544 -0.0574 0.2076 1.0000
15.750 1.7390 0.05371 0.04705 -0.0567 0.2037 1.0000
16.000 1.7273 0.05735 0.05090 -0.0564 0.1998 1.0000
16.250 1.7221 0.06043 0.05409 -0.0562 0.1957 1.0000
16.500 1.7281 0.06225 0.05584 -0.0558 0.1913 1.0000
16.750 1.7173 0.06619 0.05995 -0.0560 0.1872 1.0000
17.000 1.7052 0.07043 0.06434 -0.0565 0.1825 1.0000
17.250 1.7061 0.07301 0.06689 -0.0565 0.1778 1.0000
17.500 1.6917 0.07780 0.07183 -0.0574 0.1730 1.0000
17.750 1.6775 0.08272 0.07688 -0.0586 0.1677 1.0000
18.000 1.6774 0.08559 0.07967 -0.0589 0.1621 1.0000
18.250 1.6530 0.09227 0.08658 -0.0610 0.1563 1.0000
18.500 1.6546 0.09493 0.08911 -0.0614 0.1502 1.0000
18.750 1.6267 0.10250 0.09692 -0.0642 0.1440 1.0000
19.000 1.6265 0.10555 0.09983 -0.0649 0.1381 1.0000
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Polar data table (+)
Polar graphs
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