GOE 497 AIRFOIL (goe497-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 497 AIRFOIL (goe497-il) Reynolds number: 500,000 Max Cl/Cd: 105.32 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe497-il-500000-n5.txt Download as CSV file: xf-goe497-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 497 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6602 0.08251 0.07949 -0.0736 1.0000 0.0229
-14.500 -0.6857 0.07572 0.07266 -0.0769 1.0000 0.0231
-14.250 -0.7154 0.06898 0.06584 -0.0800 1.0000 0.0232
-14.000 -0.7476 0.06301 0.05982 -0.0821 1.0000 0.0233
-13.750 -0.7626 0.05510 0.05180 -0.0909 0.9964 0.0235
-13.500 -0.7747 0.04753 0.04410 -0.1000 0.9884 0.0237
-13.250 -0.7839 0.04003 0.03645 -0.1102 0.9776 0.0239
-13.000 -0.7705 0.03289 0.02911 -0.1234 0.9705 0.0245
-12.750 -0.7451 0.02725 0.02320 -0.1352 0.9627 0.0252
-12.500 -0.7131 0.02509 0.02083 -0.1404 0.9587 0.0261
-12.250 -0.6880 0.02364 0.01920 -0.1427 0.9507 0.0267
-12.000 -0.6595 0.02213 0.01759 -0.1456 0.9453 0.0275
-11.750 -0.6341 0.02111 0.01648 -0.1469 0.9389 0.0282
-11.500 -0.6073 0.02032 0.01560 -0.1480 0.9328 0.0290
-11.000 -0.5549 0.01887 0.01391 -0.1494 0.9209 0.0307
-10.750 -0.5284 0.01824 0.01314 -0.1498 0.9148 0.0314
-10.500 -0.5034 0.01747 0.01229 -0.1502 0.9088 0.0323
-10.250 -0.4785 0.01687 0.01162 -0.1503 0.9020 0.0331
-10.000 -0.4518 0.01637 0.01103 -0.1506 0.8964 0.0340
-9.750 -0.4261 0.01590 0.01048 -0.1506 0.8906 0.0348
-9.500 -0.4000 0.01545 0.00993 -0.1506 0.8847 0.0358
-9.250 -0.3730 0.01503 0.00940 -0.1507 0.8795 0.0366
-9.000 -0.3473 0.01457 0.00885 -0.1506 0.8737 0.0374
-8.750 -0.3213 0.01405 0.00827 -0.1506 0.8676 0.0384
-8.500 -0.2943 0.01364 0.00780 -0.1506 0.8623 0.0394
-8.250 -0.2678 0.01330 0.00740 -0.1505 0.8565 0.0405
-8.000 -0.2407 0.01298 0.00700 -0.1505 0.8510 0.0417
-7.750 -0.2132 0.01267 0.00659 -0.1505 0.8460 0.0427
-7.500 -0.1863 0.01236 0.00622 -0.1504 0.8399 0.0437
-7.250 -0.1594 0.01198 0.00578 -0.1503 0.8333 0.0452
-7.000 -0.1322 0.01169 0.00544 -0.1502 0.8269 0.0468
-6.750 -0.1049 0.01144 0.00512 -0.1501 0.8195 0.0486
-6.250 -0.0499 0.01096 0.00452 -0.1499 0.8069 0.0528
-6.000 -0.0223 0.01072 0.00424 -0.1499 0.8007 0.0555
-5.750 0.0054 0.01054 0.00399 -0.1498 0.7947 0.0583
-5.500 0.0330 0.01033 0.00376 -0.1497 0.7876 0.0618
-5.250 0.0607 0.01015 0.00354 -0.1496 0.7812 0.0667
-5.000 0.0885 0.00996 0.00335 -0.1495 0.7744 0.0728
-4.750 0.1162 0.00982 0.00319 -0.1494 0.7672 0.0803
-4.500 0.1440 0.00967 0.00304 -0.1493 0.7604 0.0888
-4.250 0.1718 0.00955 0.00290 -0.1492 0.7531 0.0956
-4.000 0.1996 0.00946 0.00276 -0.1490 0.7469 0.1030
-3.750 0.2275 0.00934 0.00264 -0.1489 0.7393 0.1099
-3.250 0.2827 0.00916 0.00242 -0.1486 0.7220 0.1257
-3.000 0.3101 0.00910 0.00232 -0.1484 0.7135 0.1347
-2.750 0.3378 0.00900 0.00224 -0.1483 0.7051 0.1460
-2.500 0.3653 0.00893 0.00217 -0.1481 0.6981 0.1596
-2.250 0.3932 0.00886 0.00212 -0.1480 0.6908 0.1748
-2.000 0.4207 0.00881 0.00208 -0.1478 0.6834 0.1920
-1.750 0.4482 0.00876 0.00206 -0.1476 0.6752 0.2117
-1.500 0.4753 0.00875 0.00204 -0.1474 0.6664 0.2275
-1.250 0.5029 0.00874 0.00203 -0.1472 0.6579 0.2399
-0.750 0.5574 0.00877 0.00204 -0.1467 0.6407 0.2652
-0.500 0.5842 0.00880 0.00205 -0.1463 0.6315 0.2766
-0.250 0.6114 0.00883 0.00207 -0.1461 0.6222 0.2871
0.000 0.6383 0.00887 0.00210 -0.1458 0.6139 0.2984
0.250 0.6654 0.00890 0.00214 -0.1455 0.6047 0.3094
0.500 0.6923 0.00896 0.00219 -0.1452 0.5963 0.3207
0.750 0.7190 0.00901 0.00224 -0.1448 0.5859 0.3345
1.000 0.7455 0.00905 0.00231 -0.1445 0.5748 0.3515
1.250 0.7716 0.00912 0.00239 -0.1440 0.5626 0.3695
1.500 0.7973 0.00921 0.00247 -0.1435 0.5488 0.3867
1.750 0.8227 0.00931 0.00256 -0.1430 0.5328 0.4034
2.000 0.8476 0.00945 0.00267 -0.1423 0.5142 0.4185
2.250 0.8718 0.00962 0.00280 -0.1415 0.4945 0.4329
2.500 0.8961 0.00980 0.00293 -0.1408 0.4784 0.4469
2.750 0.9200 0.01000 0.00309 -0.1400 0.4631 0.4625
3.000 0.9439 0.01020 0.00327 -0.1392 0.4493 0.4787
3.250 0.9681 0.01038 0.00344 -0.1385 0.4387 0.4948
3.500 0.9933 0.01051 0.00360 -0.1379 0.4315 0.5138
3.750 1.0181 0.01063 0.00378 -0.1373 0.4246 0.5363
4.000 1.0426 0.01076 0.00397 -0.1366 0.4186 0.5642
4.250 1.0676 0.01081 0.00416 -0.1361 0.4129 0.6098
4.500 1.0884 0.01061 0.00441 -0.1346 0.4071 0.7835
5.000 1.1374 0.01080 0.00479 -0.1332 0.3874 1.0000
5.250 1.1604 0.01106 0.00499 -0.1323 0.3730 1.0000
5.500 1.1833 0.01131 0.00520 -0.1314 0.3598 1.0000
5.750 1.2057 0.01157 0.00542 -0.1304 0.3471 1.0000
6.000 1.2273 0.01186 0.00566 -0.1292 0.3318 1.0000
6.250 1.2461 0.01226 0.00595 -0.1276 0.3081 1.0000
6.500 1.2602 0.01280 0.00632 -0.1252 0.2784 1.0000
6.750 1.2751 0.01331 0.00672 -0.1229 0.2592 1.0000
7.000 1.2907 0.01380 0.00713 -0.1208 0.2446 1.0000
7.250 1.3079 0.01423 0.00752 -0.1190 0.2340 1.0000
7.500 1.3249 0.01467 0.00794 -0.1172 0.2252 1.0000
7.750 1.3423 0.01510 0.00835 -0.1154 0.2172 1.0000
8.000 1.3592 0.01555 0.00880 -0.1137 0.2104 1.0000
8.250 1.3772 0.01596 0.00922 -0.1121 0.2035 1.0000
8.500 1.3928 0.01650 0.00973 -0.1103 0.1955 1.0000
8.750 1.4099 0.01696 0.01021 -0.1087 0.1854 1.0000
9.000 1.4240 0.01760 0.01079 -0.1067 0.1695 1.0000
9.250 1.4319 0.01861 0.01160 -0.1040 0.1393 1.0000
9.500 1.4374 0.01979 0.01262 -0.1011 0.1152 1.0000
9.750 1.4463 0.02080 0.01358 -0.0987 0.1026 1.0000
10.000 1.4578 0.02169 0.01446 -0.0967 0.0951 1.0000
10.250 1.4686 0.02264 0.01540 -0.0948 0.0883 1.0000
10.500 1.4809 0.02352 0.01630 -0.0930 0.0838 1.0000
10.750 1.4927 0.02446 0.01726 -0.0913 0.0793 1.0000
11.000 1.5026 0.02556 0.01837 -0.0895 0.0747 1.0000
11.250 1.5146 0.02653 0.01938 -0.0880 0.0708 1.0000
11.500 1.5249 0.02766 0.02053 -0.0864 0.0673 1.0000
11.750 1.5342 0.02889 0.02178 -0.0847 0.0642 1.0000
12.000 1.5455 0.03000 0.02295 -0.0834 0.0616 1.0000
12.250 1.5552 0.03127 0.02425 -0.0820 0.0586 1.0000
12.500 1.5625 0.03275 0.02575 -0.0805 0.0553 1.0000
12.750 1.5720 0.03410 0.02716 -0.0792 0.0530 1.0000
13.000 1.5805 0.03557 0.02868 -0.0780 0.0502 1.0000
13.250 1.5868 0.03727 0.03040 -0.0767 0.0472 1.0000
13.500 1.5942 0.03893 0.03212 -0.0756 0.0446 1.0000
13.750 1.6001 0.04078 0.03401 -0.0745 0.0408 1.0000
14.000 1.6047 0.04281 0.03607 -0.0735 0.0367 1.0000
14.250 1.6072 0.04512 0.03840 -0.0726 0.0315 1.0000
14.500 1.6065 0.04785 0.04113 -0.0717 0.0253 1.0000
14.750 1.6051 0.05077 0.04407 -0.0710 0.0212 1.0000
15.000 1.6040 0.05376 0.04711 -0.0704 0.0189 1.0000
15.250 1.6031 0.05681 0.05024 -0.0700 0.0173 1.0000
15.500 1.6020 0.05999 0.05349 -0.0698 0.0162 1.0000
15.750 1.6018 0.06314 0.05673 -0.0697 0.0154 1.0000
16.000 1.6009 0.06648 0.06016 -0.0698 0.0148 1.0000
16.250 1.5982 0.07012 0.06390 -0.0701 0.0141 1.0000
16.500 1.5943 0.07404 0.06791 -0.0705 0.0135 1.0000
16.750 1.5916 0.07790 0.07188 -0.0711 0.0132 1.0000
17.000 1.5893 0.08180 0.07588 -0.0718 0.0128 1.0000
17.250 1.5861 0.08589 0.08009 -0.0727 0.0123 1.0000
17.500 1.5821 0.09020 0.08452 -0.0738 0.0120 1.0000
17.750 1.5773 0.09471 0.08914 -0.0751 0.0117 1.0000
18.000 1.5715 0.09946 0.09399 -0.0765 0.0114 1.0000
18.250 1.5650 0.10441 0.09905 -0.0782 0.0112 1.0000
18.500 1.5573 0.10958 0.10432 -0.0801 0.0110 1.0000
18.750 1.5485 0.11503 0.10989 -0.0822 0.0107 1.0000
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Polar data table (+)
Polar graphs
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