GOE 449 AIRFOIL (goe449-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 449 AIRFOIL (goe449-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.86 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe449-il-1000000.txt Download as CSV file: xf-goe449-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 449 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6807 0.07340 0.07085 -0.1092 0.9942 0.0264
-16.500 -0.7311 0.06027 0.05748 -0.1202 0.9914 0.0263
-16.250 -0.7502 0.05173 0.04875 -0.1288 0.9882 0.0264
-16.000 -0.7600 0.04448 0.04131 -0.1372 0.9850 0.0265
-15.750 -0.7573 0.03912 0.03577 -0.1445 0.9824 0.0267
-15.500 -0.7551 0.03533 0.03184 -0.1486 0.9762 0.0268
-15.250 -0.7456 0.03232 0.02869 -0.1524 0.9713 0.0270
-15.000 -0.7303 0.03006 0.02629 -0.1557 0.9664 0.0271
-14.750 -0.7212 0.02718 0.02323 -0.1589 0.9586 0.0274
-14.500 -0.6979 0.02479 0.02071 -0.1632 0.9545 0.0277
-14.250 -0.6732 0.02328 0.01910 -0.1660 0.9466 0.0280
-14.000 -0.6409 0.02218 0.01794 -0.1693 0.9403 0.0284
-13.750 -0.6168 0.02127 0.01693 -0.1706 0.9297 0.0287
-13.500 -0.5939 0.02053 0.01609 -0.1713 0.9193 0.0291
-13.250 -0.5786 0.01983 0.01527 -0.1704 0.9072 0.0294
-13.000 -0.5685 0.01926 0.01459 -0.1681 0.8957 0.0297
-12.750 -0.5566 0.01876 0.01399 -0.1659 0.8861 0.0300
-12.500 -0.5479 0.01824 0.01337 -0.1630 0.8766 0.0302
-12.250 -0.5370 0.01783 0.01285 -0.1604 0.8686 0.0305
-12.000 -0.5273 0.01743 0.01237 -0.1574 0.8606 0.0307
-11.750 -0.5127 0.01703 0.01185 -0.1553 0.8531 0.0309
-11.500 -0.4972 0.01667 0.01143 -0.1533 0.8464 0.0310
-11.250 -0.4845 0.01603 0.01069 -0.1509 0.8393 0.0314
-11.000 -0.4712 0.01539 0.00998 -0.1487 0.8331 0.0319
-10.750 -0.4541 0.01497 0.00952 -0.1470 0.8276 0.0324
-10.500 -0.4352 0.01460 0.00910 -0.1455 0.8223 0.0327
-10.250 -0.4148 0.01431 0.00875 -0.1442 0.8169 0.0332
-10.000 -0.3948 0.01397 0.00838 -0.1429 0.8121 0.0336
-9.750 -0.3740 0.01366 0.00801 -0.1417 0.8070 0.0341
-9.500 -0.3525 0.01337 0.00765 -0.1406 0.8022 0.0346
-9.250 -0.3305 0.01310 0.00732 -0.1395 0.7976 0.0350
-9.000 -0.3081 0.01284 0.00701 -0.1385 0.7932 0.0353
-8.750 -0.2876 0.01244 0.00656 -0.1372 0.7886 0.0359
-8.500 -0.2664 0.01208 0.00615 -0.1360 0.7845 0.0367
-8.250 -0.2435 0.01180 0.00585 -0.1352 0.7809 0.0374
-8.000 -0.2199 0.01157 0.00561 -0.1344 0.7774 0.0382
-7.750 -0.1959 0.01136 0.00537 -0.1336 0.7737 0.0391
-7.500 -0.1716 0.01117 0.00513 -0.1329 0.7700 0.0398
-7.250 -0.1477 0.01095 0.00485 -0.1322 0.7658 0.0408
-7.000 -0.1243 0.01067 0.00458 -0.1313 0.7625 0.0422
-6.750 -0.1000 0.01047 0.00438 -0.1306 0.7588 0.0435
-6.500 -0.0751 0.01031 0.00419 -0.1300 0.7551 0.0449
-6.250 -0.0508 0.01010 0.00395 -0.1293 0.7515 0.0470
-6.000 -0.0255 0.00996 0.00378 -0.1288 0.7474 0.0495
-5.750 -0.0007 0.00978 0.00362 -0.1281 0.7444 0.0525
-5.500 0.0242 0.00961 0.00348 -0.1275 0.7408 0.0564
-5.250 0.0491 0.00946 0.00334 -0.1269 0.7366 0.0609
-5.000 0.0748 0.00939 0.00323 -0.1264 0.7325 0.0652
-4.750 0.1000 0.00926 0.00312 -0.1258 0.7285 0.0703
-4.500 0.1257 0.00916 0.00303 -0.1253 0.7248 0.0741
-4.250 0.1506 0.00903 0.00292 -0.1247 0.7207 0.0789
-4.000 0.1763 0.00897 0.00284 -0.1242 0.7164 0.0824
-3.750 0.2014 0.00888 0.00274 -0.1237 0.7118 0.0871
-3.500 0.2266 0.00877 0.00266 -0.1231 0.7074 0.0915
-3.250 0.2516 0.00868 0.00257 -0.1224 0.7024 0.0962
-3.000 0.2761 0.00861 0.00249 -0.1217 0.6973 0.1016
-2.750 0.3014 0.00855 0.00242 -0.1211 0.6926 0.1066
-2.500 0.3258 0.00843 0.00235 -0.1204 0.6869 0.1142
-2.250 0.3497 0.00836 0.00228 -0.1196 0.6809 0.1235
-2.000 0.3737 0.00828 0.00222 -0.1187 0.6748 0.1352
-1.750 0.3971 0.00816 0.00217 -0.1178 0.6680 0.1552
-1.500 0.4188 0.00808 0.00213 -0.1166 0.6608 0.1803
-1.250 0.4419 0.00794 0.00210 -0.1156 0.6532 0.2109
-1.000 0.4625 0.00786 0.00207 -0.1141 0.6445 0.2431
-0.750 0.4845 0.00776 0.00206 -0.1129 0.6353 0.2764
-0.500 0.5037 0.00769 0.00204 -0.1111 0.6255 0.3143
-0.250 0.5214 0.00749 0.00204 -0.1091 0.6145 0.3860
0.000 0.5378 0.00735 0.00207 -0.1068 0.6040 0.4644
0.250 0.5512 0.00729 0.00208 -0.1038 0.5930 0.5118
0.500 0.5631 0.00702 0.00212 -0.1005 0.5833 0.6172
0.750 0.5743 0.00691 0.00221 -0.0970 0.5742 0.7102
1.000 0.5892 0.00685 0.00231 -0.0942 0.5663 0.7691
1.250 0.6010 0.00684 0.00246 -0.0907 0.5584 0.8344
1.500 0.6207 0.00686 0.00261 -0.0888 0.5523 0.8892
1.750 0.6407 0.00698 0.00274 -0.0871 0.5454 0.9203
2.000 0.6677 0.00711 0.00287 -0.0869 0.5392 0.9412
2.250 0.7053 0.00727 0.00301 -0.0891 0.5314 0.9578
2.500 0.7540 0.00755 0.00322 -0.0938 0.5233 0.9713
2.750 0.7991 0.00772 0.00337 -0.0976 0.5183 0.9783
3.000 0.8400 0.00792 0.00354 -0.1006 0.5133 0.9831
3.250 0.8789 0.00815 0.00371 -0.1032 0.5081 0.9870
3.500 0.9153 0.00830 0.00384 -0.1052 0.5037 0.9908
3.750 0.9523 0.00844 0.00397 -0.1074 0.4990 0.9943
4.000 0.9908 0.00862 0.00411 -0.1099 0.4937 0.9974
4.250 1.0296 0.00882 0.00427 -0.1126 0.4881 0.9996
4.500 1.0454 0.00887 0.00433 -0.1104 0.4843 1.0000
4.750 1.0516 0.00893 0.00439 -0.1062 0.4801 1.0000
5.000 1.0584 0.00905 0.00449 -0.1021 0.4755 1.0000
5.250 1.0693 0.00920 0.00461 -0.0989 0.4702 1.0000
5.500 1.0870 0.00930 0.00473 -0.0970 0.4652 1.0000
5.750 1.1033 0.00947 0.00488 -0.0950 0.4602 1.0000
6.000 1.1183 0.00971 0.00509 -0.0927 0.4550 1.0000
6.250 1.1388 0.00985 0.00524 -0.0915 0.4505 1.0000
6.500 1.1575 0.01003 0.00543 -0.0900 0.4450 1.0000
6.750 1.1725 0.01034 0.00569 -0.0878 0.4379 1.0000
7.000 1.1929 0.01052 0.00589 -0.0867 0.4314 1.0000
7.250 1.2099 0.01082 0.00616 -0.0850 0.4241 1.0000
7.500 1.2276 0.01111 0.00644 -0.0834 0.4170 1.0000
7.750 1.2452 0.01142 0.00674 -0.0819 0.4085 1.0000
8.000 1.2616 0.01179 0.00709 -0.0803 0.4002 1.0000
8.250 1.2775 0.01221 0.00747 -0.0786 0.3899 1.0000
8.500 1.2938 0.01263 0.00787 -0.0770 0.3800 1.0000
8.750 1.3076 0.01316 0.00837 -0.0751 0.3692 1.0000
9.000 1.3224 0.01369 0.00886 -0.0734 0.3576 1.0000
9.250 1.3370 0.01425 0.00940 -0.0718 0.3466 1.0000
9.500 1.3498 0.01491 0.01001 -0.0699 0.3349 1.0000
9.750 1.3620 0.01562 0.01067 -0.0681 0.3232 1.0000
10.000 1.3760 0.01627 0.01130 -0.0665 0.3122 1.0000
10.250 1.3875 0.01708 0.01207 -0.0647 0.3003 1.0000
10.500 1.3979 0.01796 0.01290 -0.0628 0.2884 1.0000
10.750 1.4083 0.01887 0.01376 -0.0610 0.2757 1.0000
11.000 1.4208 0.01969 0.01456 -0.0595 0.2660 1.0000
11.250 1.4304 0.02070 0.01554 -0.0577 0.2556 1.0000
11.500 1.4387 0.02182 0.01661 -0.0559 0.2435 1.0000
11.750 1.4504 0.02276 0.01753 -0.0545 0.2344 1.0000
12.000 1.4586 0.02394 0.01868 -0.0528 0.2252 1.0000
12.250 1.4692 0.02499 0.01972 -0.0515 0.2161 1.0000
12.500 1.4782 0.02620 0.02091 -0.0500 0.2079 1.0000
12.750 1.4871 0.02740 0.02210 -0.0486 0.1992 1.0000
13.000 1.4954 0.02870 0.02338 -0.0472 0.1904 1.0000
13.250 1.5022 0.03012 0.02477 -0.0457 0.1820 1.0000
13.500 1.5091 0.03159 0.02623 -0.0444 0.1720 1.0000
13.750 1.5148 0.03315 0.02777 -0.0430 0.1633 1.0000
14.000 1.5170 0.03501 0.02959 -0.0414 0.1528 1.0000
14.250 1.5230 0.03665 0.03123 -0.0402 0.1457 1.0000
14.500 1.5264 0.03850 0.03306 -0.0389 0.1387 1.0000
14.750 1.5324 0.04021 0.03479 -0.0379 0.1341 1.0000
15.000 1.5352 0.04218 0.03677 -0.0367 0.1286 1.0000
15.250 1.5408 0.04398 0.03859 -0.0358 0.1247 1.0000
15.500 1.5462 0.04581 0.04045 -0.0350 0.1212 1.0000
15.750 1.5494 0.04788 0.04253 -0.0341 0.1176 1.0000
16.000 1.5520 0.05004 0.04474 -0.0332 0.1141 1.0000
16.250 1.5593 0.05178 0.04652 -0.0327 0.1113 1.0000
16.500 1.5622 0.05396 0.04874 -0.0320 0.1080 1.0000
16.750 1.5629 0.05639 0.05118 -0.0313 0.1046 1.0000
17.000 1.5668 0.05855 0.05339 -0.0308 0.1018 1.0000
17.250 1.5715 0.06064 0.05553 -0.0304 0.0986 1.0000
17.500 1.5723 0.06313 0.05804 -0.0300 0.0947 1.0000
17.750 1.5721 0.06578 0.06072 -0.0296 0.0913 1.0000
18.000 1.5756 0.06805 0.06303 -0.0293 0.0876 1.0000
18.250 1.5723 0.07108 0.06606 -0.0290 0.0823 1.0000
18.500 1.5716 0.07387 0.06888 -0.0288 0.0774 1.0000
18.750 1.5660 0.07718 0.07219 -0.0286 0.0713 1.0000
19.000 1.5589 0.08072 0.07573 -0.0284 0.0654 1.0000
19.250 1.5526 0.08424 0.07927 -0.0284 0.0607 1.0000
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