GOE 511 AIRFOIL (goe511-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 511 AIRFOIL (goe511-il) Reynolds number: 1,000,000 Max Cl/Cd: 87.34 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe511-il-1000000.txt Download as CSV file: xf-goe511-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 511 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
------ -------- --------- --------- -------- -------- --------
-13.000 0.1989 0.09482 0.09291 -0.1402 0.9517 0.0247
-12.750 0.2111 0.09285 0.09093 -0.1404 0.9472 0.0249
-12.500 0.1323 0.09936 0.09738 -0.1380 0.9572 0.0247
-12.250 0.1535 0.09708 0.09509 -0.1403 0.9558 0.0249
-12.000 0.1651 0.09512 0.09313 -0.1409 0.9515 0.0251
-11.750 0.1759 0.09308 0.09109 -0.1417 0.9468 0.0254
-11.500 0.1909 0.09024 0.08823 -0.1445 0.9432 0.0257
-11.250 0.2075 0.08731 0.08528 -0.1478 0.9407 0.0264
-11.000 0.1886 0.07907 0.07703 -0.1537 0.9369 0.0284
-10.750 0.1962 0.07710 0.07505 -0.1538 0.9308 0.0286
-10.500 0.2119 0.07479 0.07273 -0.1560 0.9271 0.0287
-10.250 0.2355 0.07311 0.07101 -0.1586 0.9226 0.0290
-10.000 0.2406 0.07136 0.06927 -0.1582 0.9151 0.0292
-9.750 0.2557 0.06871 0.06659 -0.1612 0.9094 0.0296
-9.500 0.2667 0.06626 0.06412 -0.1633 0.9027 0.0303
-9.250 0.2401 0.05461 0.05244 -0.1763 0.8934 0.0327
-9.000 0.2381 0.05124 0.04903 -0.1793 0.8838 0.0328
-8.750 0.2456 0.04973 0.04746 -0.1795 0.8724 0.0330
-8.500 0.2404 0.04821 0.04589 -0.1771 0.8569 0.0332
-8.250 0.2284 0.04634 0.04393 -0.1737 0.8323 0.0334
-8.000 0.2096 0.04480 0.04208 -0.1682 0.7692 0.0335
-7.750 0.1970 0.04413 0.04116 -0.1625 0.7256 0.0338
-7.500 -0.0116 0.01794 0.01310 -0.1364 0.7340 0.0299
-7.250 -0.0095 0.01759 0.01257 -0.1310 0.7116 0.0301
-7.000 -0.0069 0.01718 0.01200 -0.1257 0.6940 0.0303
-6.750 -0.0015 0.01678 0.01144 -0.1210 0.6771 0.0305
-6.500 0.0060 0.01635 0.01085 -0.1167 0.6595 0.0308
-6.250 0.0126 0.01597 0.01030 -0.1122 0.6389 0.0312
-6.000 0.0198 0.01553 0.00969 -0.1078 0.6174 0.0313
-5.750 0.0283 0.01517 0.00914 -0.1037 0.5943 0.0315
-5.500 0.0392 0.01491 0.00870 -0.1001 0.5741 0.0317
-5.250 0.0521 0.01463 0.00828 -0.0968 0.5591 0.0319
-5.000 0.0673 0.01438 0.00789 -0.0941 0.5468 0.0321
-4.750 0.0855 0.01410 0.00751 -0.0919 0.5378 0.0322
-4.500 0.1036 0.01397 0.00727 -0.0897 0.5290 0.0324
-4.250 0.1218 0.01324 0.00646 -0.0877 0.5222 0.0329
-4.000 0.1418 0.01295 0.00613 -0.0859 0.5157 0.0332
-3.750 0.1605 0.01279 0.00591 -0.0839 0.5089 0.0335
-3.500 0.1811 0.01266 0.00576 -0.0823 0.5030 0.0339
-3.250 0.2028 0.01256 0.00563 -0.0809 0.4978 0.0346
-3.000 0.2230 0.01245 0.00546 -0.0791 0.4915 0.0349
-2.750 0.2433 0.01237 0.00533 -0.0774 0.4859 0.0354
-2.500 0.2660 0.01222 0.00516 -0.0762 0.4816 0.0358
-2.250 0.2876 0.01210 0.00501 -0.0748 0.4767 0.0362
-2.000 0.3078 0.01205 0.00491 -0.0730 0.4712 0.0366
-1.750 0.3285 0.01201 0.00484 -0.0714 0.4660 0.0370
-1.500 0.3494 0.01175 0.00457 -0.0699 0.4618 0.0376
-1.250 0.3703 0.01165 0.00446 -0.0683 0.4564 0.0384
-1.000 0.3904 0.01164 0.00441 -0.0667 0.4507 0.0391
-0.750 0.4122 0.01161 0.00437 -0.0653 0.4458 0.0397
-0.500 0.4341 0.01157 0.00431 -0.0640 0.4401 0.0407
-0.250 0.4543 0.01159 0.00428 -0.0624 0.4340 0.0414
0.000 0.4742 0.01157 0.00423 -0.0607 0.4283 0.0427
0.250 0.4955 0.01154 0.00421 -0.0593 0.4228 0.0443
0.500 0.5155 0.01157 0.00421 -0.0577 0.4166 0.0456
0.750 0.5356 0.01164 0.00424 -0.0561 0.4106 0.0473
1.000 0.5567 0.01161 0.00421 -0.0547 0.4052 0.0497
1.250 0.5765 0.01167 0.00424 -0.0531 0.3988 0.0529
1.500 0.5953 0.01172 0.00428 -0.0512 0.3929 0.0595
1.750 0.6118 0.01153 0.00432 -0.0490 0.3881 0.1299
2.000 0.6294 0.01156 0.00450 -0.0471 0.3824 0.1997
2.250 0.6483 0.01172 0.00465 -0.0454 0.3761 0.2124
2.500 0.6706 0.01183 0.00475 -0.0444 0.3722 0.2200
2.750 0.6914 0.01195 0.00487 -0.0431 0.3675 0.2281
3.000 0.7110 0.01212 0.00502 -0.0416 0.3625 0.2346
3.250 0.7309 0.01231 0.00518 -0.0402 0.3581 0.2401
3.500 0.7521 0.01241 0.00531 -0.0390 0.3545 0.2473
3.750 0.7728 0.01256 0.00546 -0.0378 0.3513 0.2529
4.000 0.7925 0.01276 0.00562 -0.0364 0.3471 0.2575
4.250 0.8114 0.01297 0.00582 -0.0349 0.3431 0.2646
4.500 0.8325 0.01312 0.00599 -0.0339 0.3407 0.2721
4.750 0.8544 0.01326 0.00614 -0.0329 0.3385 0.2774
5.000 0.8751 0.01341 0.00633 -0.0318 0.3360 0.2863
5.250 0.8955 0.01360 0.00652 -0.0307 0.3337 0.2952
5.500 0.9152 0.01380 0.00675 -0.0295 0.3309 0.3111
5.750 1.1293 0.01354 0.00806 -0.0712 0.3232 0.9900
6.000 1.1825 0.01391 0.00841 -0.0771 0.3201 0.9960
6.250 1.2359 0.01423 0.00869 -0.0831 0.3176 0.9991
6.500 1.2673 0.01451 0.00896 -0.0846 0.3150 1.0000
6.750 1.2822 0.01481 0.00924 -0.0825 0.3125 1.0000
7.000 1.2969 0.01515 0.00955 -0.0804 0.3102 1.0000
7.250 1.3131 0.01544 0.00983 -0.0787 0.3076 1.0000
7.500 1.3310 0.01566 0.01008 -0.0772 0.3063 1.0000
7.750 1.3486 0.01590 0.01034 -0.0757 0.3048 1.0000
8.000 1.3661 0.01616 0.01062 -0.0743 0.3034 1.0000
8.250 1.3834 0.01644 0.01091 -0.0728 0.3019 1.0000
8.500 1.4002 0.01675 0.01123 -0.0713 0.3002 1.0000
8.750 1.4153 0.01713 0.01160 -0.0695 0.2978 1.0000
9.000 1.4295 0.01756 0.01202 -0.0677 0.2951 1.0000
9.250 1.4434 0.01803 0.01248 -0.0658 0.2927 1.0000
9.500 1.4600 0.01840 0.01287 -0.0644 0.2913 1.0000
9.750 1.4778 0.01871 0.01322 -0.0633 0.2901 1.0000
10.000 1.4950 0.01906 0.01361 -0.0620 0.2888 1.0000
10.250 1.5122 0.01942 0.01400 -0.0608 0.2873 1.0000
10.500 1.5292 0.01980 0.01440 -0.0596 0.2858 1.0000
10.750 1.5445 0.02026 0.01488 -0.0582 0.2840 1.0000
11.000 1.5591 0.02076 0.01540 -0.0568 0.2821 1.0000
11.250 1.5730 0.02133 0.01597 -0.0553 0.2799 1.0000
11.500 1.5839 0.02205 0.01670 -0.0534 0.2769 1.0000
11.750 1.5988 0.02260 0.01728 -0.0522 0.2753 1.0000
12.000 1.6165 0.02301 0.01774 -0.0513 0.2736 1.0000
12.250 1.6330 0.02350 0.01827 -0.0504 0.2714 1.0000
12.500 1.6474 0.02411 0.01891 -0.0492 0.2691 1.0000
12.750 1.6604 0.02481 0.01963 -0.0479 0.2660 1.0000
13.000 1.6701 0.02573 0.02055 -0.0463 0.2626 1.0000
13.250 1.6813 0.02659 0.02144 -0.0449 0.2599 1.0000
13.500 1.6974 0.02717 0.02208 -0.0442 0.2576 1.0000
13.750 1.7108 0.02794 0.02290 -0.0432 0.2542 1.0000
14.000 1.7221 0.02887 0.02384 -0.0420 0.2509 1.0000
14.250 1.7266 0.03028 0.02525 -0.0403 0.2457 1.0000
14.500 1.7400 0.03111 0.02613 -0.0395 0.2419 1.0000
14.750 1.7493 0.03225 0.02730 -0.0384 0.2371 1.0000
15.000 1.7505 0.03403 0.02907 -0.0368 0.2307 1.0000
15.250 1.7591 0.03529 0.03037 -0.0358 0.2246 1.0000
15.500 1.7585 0.03730 0.03238 -0.0342 0.2175 1.0000
15.750 1.7596 0.03923 0.03433 -0.0329 0.2096 1.0000
16.000 1.7510 0.04202 0.03710 -0.0312 0.1996 1.0000
16.250 1.7407 0.04506 0.04014 -0.0295 0.1909 1.0000
16.500 1.7322 0.04805 0.04315 -0.0282 0.1838 1.0000
16.750 1.7163 0.05185 0.04696 -0.0267 0.1770 1.0000
17.000 1.7089 0.05491 0.05007 -0.0259 0.1724 1.0000
17.250 1.6962 0.05863 0.05383 -0.0250 0.1679 1.0000
17.500 1.6787 0.06293 0.05817 -0.0242 0.1632 1.0000
17.750 1.6743 0.06588 0.06120 -0.0238 0.1609 1.0000
18.000 1.6656 0.06932 0.06470 -0.0234 0.1578 1.0000
18.250 1.6520 0.07338 0.06881 -0.0231 0.1549 1.0000
18.500 1.6355 0.07784 0.07333 -0.0229 0.1520 1.0000
18.750 1.6243 0.08173 0.07728 -0.0228 0.1497 1.0000
19.000 1.6209 0.08471 0.08034 -0.0228 0.1475 1.0000
19.250 1.6111 0.08852 0.08421 -0.0230 0.1452 1.0000
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Polar data table (+)
Polar graphs
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