GOE 518 AIRFOIL (goe518-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 518 AIRFOIL (goe518-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.99 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe518-il-1000000.txt Download as CSV file: xf-goe518-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 518 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
------ -------- --------- --------- -------- -------- --------
-12.000 0.1594 0.09574 0.09377 -0.1381 0.9495 0.0241
-11.750 0.1512 0.08832 0.08633 -0.1448 0.9446 0.0257
-11.500 0.1632 0.08406 0.08204 -0.1485 0.9415 0.0259
-11.250 0.1736 0.08214 0.08012 -0.1489 0.9356 0.0260
-11.000 0.1894 0.08035 0.07832 -0.1502 0.9299 0.0262
-10.750 0.2063 0.07729 0.07523 -0.1538 0.9255 0.0264
-10.500 0.2169 0.07544 0.07337 -0.1545 0.9179 0.0267
-10.250 0.2312 0.07234 0.07024 -0.1580 0.9105 0.0270
-10.000 0.2217 0.06249 0.06033 -0.1696 0.8999 0.0294
-9.750 0.2253 0.05735 0.05514 -0.1748 0.8905 0.0298
-9.500 0.2340 0.05482 0.05258 -0.1771 0.8795 0.0299
-9.250 0.2377 0.05132 0.04903 -0.1814 0.8672 0.0301
-9.000 0.2295 0.04734 0.04496 -0.1847 0.8539 0.0302
-8.750 0.2220 0.04519 0.04271 -0.1833 0.8403 0.0304
-8.500 0.2004 0.04273 0.04015 -0.1790 0.8276 0.0305
-8.250 0.1946 0.04095 0.03829 -0.1760 0.8173 0.0308
-8.000 0.1175 0.03217 0.02876 -0.1648 0.8054 0.0336
-7.750 0.0930 0.02795 0.02429 -0.1581 0.7959 0.0340
-7.500 0.1039 0.02690 0.02320 -0.1556 0.7861 0.0341
-7.250 0.1150 0.02616 0.02240 -0.1529 0.7747 0.0343
-7.000 0.1249 0.02537 0.02153 -0.1499 0.7627 0.0345
-6.750 0.1350 0.02477 0.02085 -0.1468 0.7487 0.0347
-6.500 0.1423 0.02404 0.01998 -0.1431 0.7316 0.0350
-6.250 0.1474 0.02332 0.01910 -0.1388 0.7102 0.0354
-6.000 0.1203 0.01858 0.01357 -0.1282 0.6927 0.0325
-5.750 0.1188 0.01739 0.01210 -0.1223 0.6710 0.0318
-5.500 0.1161 0.01589 0.01025 -0.1159 0.6528 0.0310
-5.250 0.1234 0.01525 0.00941 -0.1115 0.6363 0.0310
-5.000 0.1340 0.01469 0.00866 -0.1078 0.6218 0.0310
-4.750 0.1456 0.01428 0.00812 -0.1044 0.6084 0.0311
-4.500 0.1611 0.01387 0.00760 -0.1017 0.5968 0.0313
-4.250 0.1772 0.01354 0.00717 -0.0991 0.5860 0.0315
-4.000 0.1928 0.01340 0.00693 -0.0965 0.5742 0.0321
-3.750 0.2106 0.01309 0.00654 -0.0943 0.5634 0.0324
-3.500 0.2266 0.01285 0.00619 -0.0917 0.5518 0.0325
-3.250 0.2439 0.01264 0.00589 -0.0894 0.5391 0.0328
-3.000 0.2617 0.01247 0.00564 -0.0872 0.5265 0.0329
-2.750 0.2782 0.01239 0.00547 -0.0848 0.5126 0.0331
-2.500 0.2939 0.01234 0.00532 -0.0822 0.4976 0.0333
-2.250 0.3100 0.01230 0.00519 -0.0797 0.4822 0.0334
-2.000 0.3279 0.01232 0.00514 -0.0776 0.4679 0.0336
-1.750 0.3435 0.01206 0.00481 -0.0750 0.4553 0.0340
-1.500 0.3586 0.01198 0.00467 -0.0724 0.4430 0.0342
-1.250 0.3754 0.01192 0.00457 -0.0701 0.4319 0.0347
-1.000 0.3929 0.01192 0.00453 -0.0680 0.4222 0.0351
-0.750 0.4109 0.01195 0.00452 -0.0660 0.4126 0.0359
-0.500 0.4295 0.01197 0.00450 -0.0641 0.4041 0.0365
-0.250 0.4474 0.01201 0.00449 -0.0621 0.3962 0.0370
0.000 0.4654 0.01207 0.00450 -0.0601 0.3889 0.0377
0.250 0.4850 0.01211 0.00451 -0.0585 0.3826 0.0380
0.500 0.5020 0.01213 0.00448 -0.0563 0.3754 0.0387
0.750 0.5214 0.01214 0.00448 -0.0546 0.3704 0.0395
1.000 0.5409 0.01219 0.00451 -0.0530 0.3652 0.0405
1.250 0.5589 0.01231 0.00459 -0.0511 0.3596 0.0414
1.500 0.5776 0.01242 0.00468 -0.0494 0.3550 0.0428
1.750 0.5982 0.01246 0.00472 -0.0480 0.3518 0.0443
2.000 0.6182 0.01253 0.00479 -0.0465 0.3481 0.0478
2.250 0.6372 0.01265 0.00490 -0.0449 0.3442 0.0513
2.500 0.6528 0.01267 0.00509 -0.0426 0.3405 0.1190
2.750 0.6667 0.01244 0.00532 -0.0402 0.3377 0.2974
3.000 0.9467 0.01203 0.00659 -0.0947 0.3290 0.9977
3.250 0.9949 0.01229 0.00677 -0.0993 0.3254 1.0000
3.500 1.0055 0.01254 0.00698 -0.0963 0.3222 1.0000
3.750 1.0206 0.01270 0.00713 -0.0940 0.3208 1.0000
4.000 1.0363 0.01285 0.00728 -0.0919 0.3196 1.0000
4.250 1.0520 0.01302 0.00744 -0.0897 0.3180 1.0000
4.500 1.0682 0.01319 0.00761 -0.0877 0.3162 1.0000
4.750 1.0843 0.01340 0.00780 -0.0857 0.3144 1.0000
5.000 1.1000 0.01363 0.00802 -0.0837 0.3125 1.0000
5.250 1.1149 0.01390 0.00827 -0.0816 0.3105 1.0000
5.500 1.1301 0.01419 0.00854 -0.0796 0.3087 1.0000
5.750 1.1441 0.01455 0.00887 -0.0774 0.3060 1.0000
6.000 1.1604 0.01484 0.00916 -0.0756 0.3046 1.0000
6.250 1.1785 0.01507 0.00940 -0.0741 0.3038 1.0000
6.500 1.1970 0.01530 0.00964 -0.0728 0.3024 1.0000
6.750 1.2150 0.01556 0.00992 -0.0714 0.3016 1.0000
7.000 1.2333 0.01583 0.01019 -0.0701 0.3000 1.0000
7.250 1.2508 0.01613 0.01050 -0.0686 0.2988 1.0000
7.500 1.2682 0.01644 0.01081 -0.0673 0.2968 1.0000
7.750 1.2851 0.01679 0.01116 -0.0658 0.2950 1.0000
8.000 1.3015 0.01718 0.01155 -0.0644 0.2933 1.0000
8.250 1.3157 0.01768 0.01202 -0.0626 0.2906 1.0000
8.500 1.3314 0.01814 0.01248 -0.0611 0.2887 1.0000
8.750 1.3503 0.01846 0.01283 -0.0601 0.2881 1.0000
9.000 1.3686 0.01881 0.01321 -0.0591 0.2873 1.0000
9.250 1.3865 0.01919 0.01362 -0.0580 0.2863 1.0000
9.500 1.4047 0.01956 0.01402 -0.0570 0.2851 1.0000
9.750 1.4228 0.01995 0.01443 -0.0561 0.2837 1.0000
10.000 1.4400 0.02038 0.01487 -0.0551 0.2818 1.0000
10.250 1.4567 0.02084 0.01536 -0.0540 0.2803 1.0000
10.500 1.4731 0.02134 0.01586 -0.0529 0.2790 1.0000
10.750 1.4885 0.02190 0.01644 -0.0517 0.2775 1.0000
11.000 1.5029 0.02253 0.01708 -0.0504 0.2758 1.0000
11.250 1.5168 0.02319 0.01773 -0.0491 0.2735 1.0000
11.500 1.5341 0.02368 0.01827 -0.0483 0.2726 1.0000
11.750 1.5512 0.02420 0.01884 -0.0475 0.2715 1.0000
12.000 1.5681 0.02473 0.01942 -0.0468 0.2701 1.0000
12.250 1.5850 0.02527 0.01999 -0.0461 0.2680 1.0000
12.500 1.6008 0.02589 0.02065 -0.0453 0.2660 1.0000
12.750 1.6151 0.02661 0.02139 -0.0443 0.2641 1.0000
13.000 1.6282 0.02742 0.02220 -0.0433 0.2617 1.0000
13.250 1.6384 0.02842 0.02320 -0.0420 0.2588 1.0000
13.500 1.6533 0.02914 0.02397 -0.0413 0.2575 1.0000
13.750 1.6698 0.02978 0.02468 -0.0407 0.2562 1.0000
14.000 1.6849 0.03053 0.02548 -0.0401 0.2539 1.0000
14.250 1.6990 0.03135 0.02634 -0.0395 0.2513 1.0000
14.500 1.7100 0.03240 0.02741 -0.0386 0.2478 1.0000
14.750 1.7155 0.03387 0.02886 -0.0373 0.2436 1.0000
15.000 1.7315 0.03461 0.02968 -0.0369 0.2416 1.0000
15.250 1.7444 0.03558 0.03071 -0.0364 0.2389 1.0000
15.500 1.7551 0.03673 0.03189 -0.0357 0.2352 1.0000
15.750 1.7615 0.03825 0.03342 -0.0348 0.2321 1.0000
16.000 1.7694 0.03965 0.03487 -0.0340 0.2282 1.0000
16.250 1.7780 0.04104 0.03629 -0.0334 0.2227 1.0000
16.500 1.7778 0.04321 0.03846 -0.0323 0.2166 1.0000
16.750 1.7848 0.04477 0.04007 -0.0317 0.2115 1.0000
17.000 1.7813 0.04733 0.04263 -0.0307 0.2038 1.0000
17.250 1.7777 0.04991 0.04523 -0.0298 0.1953 1.0000
17.500 1.7657 0.05335 0.04867 -0.0287 0.1856 1.0000
17.750 1.7474 0.05753 0.05284 -0.0275 0.1748 1.0000
18.000 1.7210 0.06265 0.05795 -0.0264 0.1632 1.0000
18.250 1.6983 0.06756 0.06289 -0.0257 0.1547 1.0000
18.500 1.6736 0.07286 0.06822 -0.0252 0.1463 1.0000
18.750 1.6461 0.07863 0.07404 -0.0250 0.1399 1.0000
19.000 1.6217 0.08420 0.07967 -0.0251 0.1342 1.0000
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