GOE 527 AIRFOIL (goe527-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 527 AIRFOIL (goe527-il) Reynolds number: 200,000 Max Cl/Cd: 69.35 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe527-il-200000-n5.txt Download as CSV file: xf-goe527-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 527 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.3891 0.03863 0.03371 -0.1350 0.8908 0.0385
-11.000 -0.3897 0.03638 0.03123 -0.1347 0.8732 0.0388
-10.750 -0.3834 0.03474 0.02939 -0.1340 0.8583 0.0392
-10.500 -0.3763 0.03314 0.02757 -0.1329 0.8450 0.0397
-10.250 -0.3690 0.03154 0.02572 -0.1315 0.8321 0.0403
-10.000 -0.3620 0.02986 0.02375 -0.1297 0.8199 0.0408
-9.750 -0.3516 0.02822 0.02179 -0.1282 0.8094 0.0414
-9.500 -0.3398 0.02670 0.01995 -0.1265 0.7987 0.0419
-9.250 -0.3248 0.02533 0.01825 -0.1251 0.7896 0.0425
-9.000 -0.3072 0.02429 0.01700 -0.1238 0.7799 0.0431
-8.750 -0.2864 0.02358 0.01621 -0.1229 0.7712 0.0436
-8.500 -0.2656 0.02299 0.01553 -0.1219 0.7617 0.0442
-8.250 -0.2438 0.02240 0.01481 -0.1210 0.7536 0.0451
-8.000 -0.2227 0.02175 0.01402 -0.1199 0.7448 0.0460
-7.750 -0.2005 0.02104 0.01311 -0.1190 0.7373 0.0470
-7.500 -0.1786 0.02034 0.01222 -0.1180 0.7290 0.0480
-7.250 -0.1558 0.01980 0.01161 -0.1172 0.7210 0.0488
-7.000 -0.1326 0.01936 0.01111 -0.1163 0.7131 0.0497
-6.750 -0.1093 0.01893 0.01060 -0.1155 0.7050 0.0508
-6.500 -0.0853 0.01849 0.01003 -0.1147 0.6981 0.0522
-6.250 -0.0616 0.01804 0.00947 -0.1139 0.6903 0.0539
-6.000 -0.0375 0.01773 0.00912 -0.1131 0.6832 0.0554
-5.750 -0.0131 0.01744 0.00878 -0.1124 0.6760 0.0574
-5.500 0.0112 0.01710 0.00834 -0.1116 0.6683 0.0598
-5.250 0.0359 0.01682 0.00800 -0.1110 0.6618 0.0620
-5.000 0.0604 0.01657 0.00774 -0.1102 0.6545 0.0649
-4.750 0.0853 0.01633 0.00742 -0.1095 0.6478 0.0684
-4.500 0.1106 0.01618 0.00722 -0.1090 0.6417 0.0722
-4.250 0.1355 0.01599 0.00699 -0.1083 0.6345 0.0767
-4.000 0.1609 0.01585 0.00680 -0.1077 0.6281 0.0812
-3.750 0.1863 0.01570 0.00658 -0.1071 0.6223 0.0860
-3.500 0.2114 0.01556 0.00644 -0.1065 0.6161 0.0907
-3.250 0.2371 0.01547 0.00624 -0.1059 0.6103 0.0958
-3.000 0.2621 0.01530 0.00607 -0.1053 0.6050 0.1008
-2.750 0.2875 0.01521 0.00594 -0.1048 0.5989 0.1065
-2.500 0.3124 0.01505 0.00578 -0.1042 0.5935 0.1125
-2.000 0.3629 0.01482 0.00552 -0.1030 0.5837 0.1261
-1.750 0.3880 0.01472 0.00541 -0.1024 0.5783 0.1333
-1.500 0.4133 0.01462 0.00530 -0.1019 0.5737 0.1412
-1.250 0.4389 0.01455 0.00522 -0.1014 0.5695 0.1529
-1.000 0.4635 0.01442 0.00521 -0.1007 0.5646 0.1744
-0.750 0.4879 0.01426 0.00519 -0.1001 0.5598 0.2174
-0.500 0.5122 0.01409 0.00518 -0.0995 0.5556 0.2789
-0.250 0.5362 0.01392 0.00520 -0.0988 0.5518 0.3492
0.000 0.5589 0.01374 0.00530 -0.0978 0.5472 0.4278
0.250 0.5814 0.01358 0.00538 -0.0967 0.5428 0.5068
0.500 0.6040 0.01344 0.00543 -0.0956 0.5387 0.5823
0.750 0.6255 0.01321 0.00552 -0.0940 0.5352 0.6913
1.000 0.6855 0.01303 0.00586 -0.0999 0.5298 0.9052
1.250 0.7349 0.01318 0.00595 -0.1042 0.5238 0.9689
1.500 0.7860 0.01335 0.00595 -0.1091 0.5174 0.9924
1.750 0.8155 0.01348 0.00605 -0.1096 0.5101 1.0000
2.000 0.8351 0.01361 0.00610 -0.1080 0.5038 1.0000
2.250 0.8563 0.01377 0.00614 -0.1067 0.4991 1.0000
2.500 0.8762 0.01391 0.00628 -0.1051 0.4940 1.0000
2.750 0.8966 0.01406 0.00640 -0.1037 0.4892 1.0000
3.000 0.9176 0.01422 0.00650 -0.1024 0.4850 1.0000
3.250 0.9393 0.01441 0.00659 -0.1013 0.4812 1.0000
3.500 0.9592 0.01457 0.00678 -0.0998 0.4766 1.0000
3.750 0.9795 0.01474 0.00695 -0.0984 0.4719 1.0000
4.000 1.0000 0.01492 0.00708 -0.0970 0.4674 1.0000
4.250 1.0211 0.01512 0.00720 -0.0958 0.4633 1.0000
4.500 1.0403 0.01530 0.00743 -0.0942 0.4580 1.0000
4.750 1.0594 0.01549 0.00761 -0.0926 0.4525 1.0000
5.000 1.0790 0.01569 0.00775 -0.0911 0.4476 1.0000
5.250 1.0977 0.01590 0.00798 -0.0895 0.4422 1.0000
5.500 1.1156 0.01611 0.00820 -0.0878 0.4364 1.0000
5.750 1.1332 0.01634 0.00839 -0.0860 0.4308 1.0000
6.000 1.1491 0.01657 0.00864 -0.0839 0.4251 1.0000
6.250 1.1632 0.01681 0.00888 -0.0815 0.4185 1.0000
6.500 1.1773 0.01708 0.00910 -0.0791 0.4122 1.0000
6.750 1.1912 0.01737 0.00943 -0.0768 0.4049 1.0000
7.000 1.2046 0.01769 0.00974 -0.0745 0.3978 1.0000
7.250 1.2189 0.01805 0.01010 -0.0724 0.3910 1.0000
7.500 1.2320 0.01844 0.01049 -0.0702 0.3836 1.0000
7.750 1.2445 0.01888 0.01091 -0.0680 0.3761 1.0000
8.000 1.2562 0.01937 0.01141 -0.0658 0.3674 1.0000
8.250 1.2671 0.01993 0.01195 -0.0635 0.3590 1.0000
8.500 1.2769 0.02056 0.01256 -0.0612 0.3499 1.0000
8.750 1.2873 0.02123 0.01324 -0.0591 0.3415 1.0000
9.000 1.2967 0.02198 0.01397 -0.0570 0.3335 1.0000
9.250 1.3071 0.02275 0.01475 -0.0552 0.3262 1.0000
9.500 1.3164 0.02361 0.01560 -0.0533 0.3188 1.0000
9.750 1.3253 0.02452 0.01652 -0.0514 0.3122 1.0000
10.000 1.3342 0.02550 0.01752 -0.0497 0.3049 1.0000
10.250 1.3409 0.02663 0.01862 -0.0479 0.2981 1.0000
10.500 1.3494 0.02772 0.01974 -0.0464 0.2908 1.0000
10.750 1.3555 0.02898 0.02099 -0.0447 0.2846 1.0000
11.000 1.3642 0.03015 0.02219 -0.0434 0.2793 1.0000
11.250 1.3721 0.03141 0.02348 -0.0421 0.2737 1.0000
11.500 1.3787 0.03276 0.02484 -0.0407 0.2688 1.0000
11.750 1.3868 0.03407 0.02618 -0.0396 0.2645 1.0000
12.000 1.3956 0.03538 0.02756 -0.0386 0.2601 1.0000
12.250 1.4028 0.03682 0.02903 -0.0375 0.2558 1.0000
12.500 1.4093 0.03833 0.03053 -0.0365 0.2519 1.0000
12.750 1.4178 0.03974 0.03201 -0.0356 0.2483 1.0000
13.000 1.4258 0.04124 0.03358 -0.0349 0.2445 1.0000
13.250 1.4325 0.04285 0.03525 -0.0341 0.2405 1.0000
13.500 1.4386 0.04452 0.03694 -0.0333 0.2369 1.0000
13.750 1.4457 0.04613 0.03856 -0.0326 0.2335 1.0000
14.000 1.4522 0.04791 0.04046 -0.0321 0.2297 1.0000
14.250 1.4576 0.04978 0.04241 -0.0315 0.2257 1.0000
14.500 1.4626 0.05169 0.04436 -0.0310 0.2220 1.0000
14.750 1.4679 0.05354 0.04620 -0.0305 0.2184 1.0000
15.000 1.4728 0.05560 0.04839 -0.0301 0.2149 1.0000
15.250 1.4767 0.05778 0.05068 -0.0299 0.2110 1.0000
15.500 1.4807 0.05993 0.05289 -0.0296 0.2073 1.0000
15.750 1.4844 0.06209 0.05506 -0.0293 0.2037 1.0000
16.000 1.4875 0.06442 0.05749 -0.0292 0.2000 1.0000
16.250 1.4890 0.06702 0.06022 -0.0292 0.1960 1.0000
16.500 1.4902 0.06964 0.06290 -0.0292 0.1918 1.0000
16.750 1.4915 0.07218 0.06544 -0.0292 0.1878 1.0000
17.000 1.4909 0.07516 0.06857 -0.0295 0.1834 1.0000
17.250 1.4888 0.07831 0.07182 -0.0298 0.1786 1.0000
17.500 1.4876 0.08132 0.07484 -0.0301 0.1743 1.0000
17.750 1.4843 0.08476 0.07841 -0.0306 0.1693 1.0000
18.000 1.4805 0.08826 0.08198 -0.0312 0.1646 1.0000
18.250 1.4782 0.09150 0.08523 -0.0318 0.1605 1.0000
18.500 1.4742 0.09516 0.08903 -0.0325 0.1561 1.0000
18.750 1.4692 0.09893 0.09286 -0.0334 0.1515 1.0000
19.000 1.4666 0.10233 0.09627 -0.0342 0.1479 1.0000
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