GOE 497 AIRFOIL (goe497-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 497 AIRFOIL (goe497-il) Reynolds number: 200,000 Max Cl/Cd: 82.04 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe497-il-200000-n5.txt Download as CSV file: xf-goe497-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5862 0.05250 0.04828 -0.0963 0.9814 0.0369
-11.250 -0.6028 0.04000 0.03532 -0.1171 0.9642 0.0371
-11.000 -0.5758 0.03686 0.03208 -0.1241 0.9596 0.0380
-10.750 -0.5544 0.03478 0.02989 -0.1277 0.9528 0.0389
-10.500 -0.5292 0.03245 0.02736 -0.1319 0.9477 0.0400
-10.250 -0.5010 0.03005 0.02463 -0.1362 0.9442 0.0414
-10.000 -0.4819 0.02815 0.02241 -0.1376 0.9367 0.0426
-9.750 -0.4551 0.02644 0.02041 -0.1397 0.9320 0.0438
-9.500 -0.4249 0.02528 0.01921 -0.1415 0.9290 0.0450
-9.250 -0.4008 0.02432 0.01815 -0.1419 0.9232 0.0460
-9.000 -0.3744 0.02334 0.01703 -0.1427 0.9180 0.0473
-8.750 -0.3445 0.02234 0.01584 -0.1440 0.9142 0.0489
-8.500 -0.3149 0.02138 0.01465 -0.1451 0.9103 0.0504
-8.250 -0.2915 0.02050 0.01367 -0.1449 0.9036 0.0516
-8.000 -0.2631 0.01971 0.01283 -0.1456 0.8992 0.0530
-7.750 -0.2324 0.01902 0.01205 -0.1466 0.8959 0.0547
-7.500 -0.2075 0.01847 0.01141 -0.1464 0.8897 0.0568
-7.250 -0.1797 0.01789 0.01069 -0.1466 0.8843 0.0589
-7.000 -0.1500 0.01722 0.00996 -0.1473 0.8803 0.0610
-6.750 -0.1235 0.01673 0.00944 -0.1472 0.8745 0.0633
-6.500 -0.0963 0.01630 0.00892 -0.1473 0.8689 0.0661
-6.250 -0.0667 0.01586 0.00838 -0.1477 0.8646 0.0695
-6.000 -0.0389 0.01545 0.00797 -0.1478 0.8596 0.0735
-5.750 -0.0120 0.01513 0.00758 -0.1477 0.8530 0.0782
-5.500 0.0177 0.01473 0.00714 -0.1480 0.8475 0.0834
-5.250 0.0445 0.01447 0.00681 -0.1478 0.8404 0.0899
-5.000 0.0726 0.01415 0.00647 -0.1478 0.8337 0.0972
-4.750 0.1020 0.01392 0.00613 -0.1480 0.8283 0.1057
-4.500 0.1283 0.01366 0.00590 -0.1477 0.8208 0.1144
-4.250 0.1573 0.01342 0.00560 -0.1478 0.8149 0.1236
-4.000 0.1847 0.01323 0.00539 -0.1477 0.8081 0.1336
-3.750 0.2124 0.01302 0.00518 -0.1476 0.8012 0.1441
-3.500 0.2414 0.01284 0.00496 -0.1477 0.7955 0.1557
-3.250 0.2680 0.01270 0.00484 -0.1473 0.7876 0.1686
-3.000 0.2968 0.01255 0.00466 -0.1474 0.7810 0.1837
-2.750 0.3235 0.01243 0.00457 -0.1470 0.7726 0.2003
-2.500 0.3518 0.01231 0.00446 -0.1470 0.7657 0.2191
-2.250 0.3792 0.01224 0.00440 -0.1468 0.7588 0.2366
-2.000 0.4069 0.01218 0.00433 -0.1466 0.7519 0.2515
-1.750 0.4352 0.01212 0.00424 -0.1465 0.7458 0.2670
-1.500 0.4621 0.01208 0.00423 -0.1462 0.7381 0.2814
-1.250 0.4903 0.01204 0.00416 -0.1461 0.7315 0.2947
-1.000 0.5171 0.01201 0.00415 -0.1458 0.7237 0.3074
-0.750 0.5450 0.01199 0.00412 -0.1456 0.7168 0.3210
-0.500 0.5722 0.01199 0.00412 -0.1453 0.7097 0.3357
-0.250 0.5995 0.01198 0.00413 -0.1450 0.7023 0.3502
0.000 0.6268 0.01199 0.00415 -0.1448 0.6947 0.3652
0.250 0.6536 0.01199 0.00417 -0.1444 0.6859 0.3834
0.500 0.6802 0.01201 0.00421 -0.1440 0.6764 0.4033
0.750 0.7071 0.01204 0.00422 -0.1436 0.6665 0.4208
1.000 0.7331 0.01207 0.00428 -0.1431 0.6559 0.4368
1.250 0.7598 0.01211 0.00433 -0.1427 0.6473 0.4532
1.500 0.7859 0.01216 0.00441 -0.1422 0.6377 0.4700
1.750 0.8119 0.01222 0.00448 -0.1417 0.6276 0.4882
2.000 0.8376 0.01228 0.00455 -0.1411 0.6167 0.5073
2.250 0.8628 0.01233 0.00466 -0.1405 0.6048 0.5282
2.500 0.8878 0.01238 0.00477 -0.1398 0.5932 0.5533
2.750 0.9122 0.01243 0.00489 -0.1390 0.5812 0.5848
3.000 0.9356 0.01243 0.00503 -0.1380 0.5685 0.6334
3.250 0.9564 0.01223 0.00519 -0.1363 0.5553 0.7722
3.500 0.9833 0.01215 0.00525 -0.1358 0.5398 1.0000
3.750 1.0074 0.01237 0.00539 -0.1350 0.5253 1.0000
4.000 1.0314 0.01261 0.00555 -0.1342 0.5122 1.0000
4.250 1.0549 0.01286 0.00574 -0.1334 0.4996 1.0000
4.500 1.0780 0.01314 0.00594 -0.1324 0.4872 1.0000
4.750 1.1011 0.01343 0.00617 -0.1315 0.4755 1.0000
5.000 1.1240 0.01373 0.00643 -0.1306 0.4651 1.0000
5.250 1.1466 0.01405 0.00670 -0.1296 0.4556 1.0000
5.500 1.1697 0.01436 0.00699 -0.1287 0.4469 1.0000
6.000 1.2127 0.01508 0.00764 -0.1264 0.4250 1.0000
6.250 1.2324 0.01548 0.00799 -0.1250 0.4112 1.0000
6.500 1.2517 0.01588 0.00836 -0.1235 0.3982 1.0000
6.750 1.2704 0.01630 0.00873 -0.1219 0.3859 1.0000
7.000 1.2889 0.01666 0.00911 -0.1203 0.3721 1.0000
7.250 1.3052 0.01704 0.00949 -0.1183 0.3570 1.0000
7.500 1.3210 0.01746 0.00991 -0.1162 0.3420 1.0000
7.750 1.3350 0.01795 0.01036 -0.1139 0.3243 1.0000
8.000 1.3474 0.01851 0.01088 -0.1114 0.3047 1.0000
8.250 1.3587 0.01917 0.01147 -0.1089 0.2859 1.0000
8.500 1.3694 0.01991 0.01214 -0.1063 0.2702 1.0000
8.750 1.3798 0.02070 0.01289 -0.1039 0.2566 1.0000
9.000 1.3896 0.02157 0.01371 -0.1014 0.2447 1.0000
9.250 1.4019 0.02237 0.01452 -0.0994 0.2339 1.0000
9.500 1.4131 0.02325 0.01540 -0.0973 0.2245 1.0000
9.750 1.4239 0.02418 0.01635 -0.0953 0.2146 1.0000
10.000 1.4357 0.02508 0.01729 -0.0934 0.2047 1.0000
10.250 1.4453 0.02614 0.01836 -0.0915 0.1937 1.0000
10.500 1.4550 0.02723 0.01947 -0.0896 0.1796 1.0000
10.750 1.4630 0.02848 0.02069 -0.0876 0.1593 1.0000
11.000 1.4659 0.03013 0.02223 -0.0854 0.1390 1.0000
11.250 1.4678 0.03194 0.02396 -0.0833 0.1243 1.0000
11.500 1.4705 0.03378 0.02577 -0.0813 0.1140 1.0000
11.750 1.4750 0.03554 0.02755 -0.0797 0.1066 1.0000
12.000 1.4778 0.03750 0.02953 -0.0780 0.1007 1.0000
12.250 1.4830 0.03931 0.03140 -0.0767 0.0955 1.0000
12.500 1.4873 0.04125 0.03340 -0.0754 0.0908 1.0000
12.750 1.4881 0.04360 0.03577 -0.0741 0.0866 1.0000
13.000 1.4951 0.04542 0.03771 -0.0731 0.0829 1.0000
13.250 1.4992 0.04757 0.03994 -0.0722 0.0792 1.0000
13.500 1.5004 0.05010 0.04251 -0.0714 0.0759 1.0000
13.750 1.5048 0.05237 0.04488 -0.0708 0.0727 1.0000
14.000 1.5092 0.05471 0.04732 -0.0702 0.0695 1.0000
14.250 1.5110 0.05738 0.05007 -0.0698 0.0666 1.0000
14.500 1.5107 0.06041 0.05315 -0.0695 0.0640 1.0000
14.750 1.5153 0.06289 0.05578 -0.0693 0.0612 1.0000
15.000 1.5173 0.06578 0.05877 -0.0692 0.0581 1.0000
15.250 1.5160 0.06915 0.06220 -0.0693 0.0555 1.0000
15.500 1.5177 0.07221 0.06537 -0.0695 0.0525 1.0000
15.750 1.5181 0.07550 0.06878 -0.0698 0.0491 1.0000
16.000 1.5150 0.07940 0.07273 -0.0704 0.0462 1.0000
16.250 1.5156 0.08281 0.07628 -0.0710 0.0424 1.0000
16.500 1.5117 0.08698 0.08052 -0.0719 0.0391 1.0000
16.750 1.5095 0.09096 0.08461 -0.0728 0.0354 1.0000
17.000 1.5044 0.09547 0.08920 -0.0740 0.0323 1.0000
17.250 1.4995 0.10005 0.09387 -0.0754 0.0295 1.0000
17.500 1.4929 0.10495 0.09885 -0.0771 0.0275 1.0000
17.750 1.4869 0.10981 0.10381 -0.0788 0.0257 1.0000
18.000 1.4795 0.11499 0.10908 -0.0808 0.0243 1.0000
18.250 1.4721 0.12023 0.11441 -0.0829 0.0232 1.0000
18.500 1.4657 0.12533 0.11964 -0.0851 0.0222 1.0000
18.750 1.4584 0.13065 0.12507 -0.0876 0.0214 1.0000
19.000 1.4505 0.13614 0.13066 -0.0903 0.0207 1.0000
19.250 1.4422 0.14179 0.13642 -0.0932 0.0201 1.0000
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