GOE 534 AIRFOIL (goe534-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 534 AIRFOIL (goe534-il) Reynolds number: 500,000 Max Cl/Cd: 91 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe534-il-500000-n5.txt Download as CSV file: xf-goe534-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 534 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.6662 0.09539 0.09208 -0.0435 1.0000 0.0274
-15.000 -0.7080 0.08432 0.08082 -0.0507 1.0000 0.0277
-14.750 -0.7330 0.07660 0.07297 -0.0558 1.0000 0.0278
-14.500 -0.7516 0.07022 0.06648 -0.0600 1.0000 0.0279
-14.250 -0.7700 0.06420 0.06037 -0.0641 1.0000 0.0280
-14.000 -0.7834 0.05950 0.05561 -0.0670 1.0000 0.0281
-13.750 -0.7977 0.05502 0.05111 -0.0696 1.0000 0.0283
-13.500 -0.8188 0.05003 0.04606 -0.0724 1.0000 0.0283
-13.250 -0.8541 0.04478 0.04075 -0.0742 1.0000 0.0283
-13.000 -0.8742 0.03925 0.03513 -0.0785 1.0000 0.0283
-12.750 -0.8793 0.03420 0.02997 -0.0833 1.0000 0.0285
-12.500 -0.8722 0.03002 0.02566 -0.0875 1.0000 0.0287
-12.250 -0.8577 0.02698 0.02248 -0.0903 1.0000 0.0290
-12.000 -0.8233 0.02495 0.02032 -0.0945 0.9963 0.0293
-11.750 -0.7894 0.02339 0.01866 -0.0977 0.9907 0.0297
-11.500 -0.7572 0.02210 0.01727 -0.1000 0.9840 0.0300
-11.250 -0.7260 0.02100 0.01607 -0.1017 0.9758 0.0304
-11.000 -0.6915 0.01999 0.01497 -0.1038 0.9671 0.0309
-10.750 -0.6564 0.01910 0.01397 -0.1058 0.9550 0.0314
-10.500 -0.6189 0.01828 0.01304 -0.1081 0.9408 0.0318
-10.250 -0.5794 0.01727 0.01195 -0.1110 0.9220 0.0323
-10.000 -0.5427 0.01649 0.01105 -0.1131 0.8943 0.0328
-9.500 -0.4880 0.01549 0.00973 -0.1128 0.8368 0.0338
-9.250 -0.4630 0.01509 0.00918 -0.1121 0.8160 0.0344
-9.000 -0.4377 0.01473 0.00868 -0.1114 0.7990 0.0349
-8.750 -0.4121 0.01438 0.00820 -0.1108 0.7846 0.0355
-8.500 -0.3864 0.01398 0.00772 -0.1102 0.7723 0.0363
-8.000 -0.3343 0.01327 0.00684 -0.1090 0.7492 0.0385
-7.750 -0.3080 0.01299 0.00646 -0.1084 0.7392 0.0397
-7.500 -0.2812 0.01265 0.00609 -0.1079 0.7292 0.0416
-7.000 -0.2275 0.01216 0.00557 -0.1069 0.7086 0.0503
-6.750 -0.2000 0.01209 0.00548 -0.1063 0.6986 0.0577
-6.500 -0.1720 0.01200 0.00535 -0.1059 0.6878 0.0621
-6.250 -0.1444 0.01196 0.00520 -0.1053 0.6760 0.0656
-6.000 -0.1166 0.01188 0.00508 -0.1048 0.6633 0.0679
-5.750 -0.0888 0.01184 0.00497 -0.1043 0.6505 0.0702
-5.500 -0.0613 0.01180 0.00483 -0.1038 0.6350 0.0722
-5.250 -0.0340 0.01174 0.00466 -0.1032 0.6169 0.0737
-5.000 -0.0071 0.01163 0.00449 -0.1026 0.5980 0.0752
-4.750 0.0199 0.01160 0.00436 -0.1020 0.5788 0.0769
-4.500 0.0469 0.01156 0.00422 -0.1014 0.5603 0.0782
-4.250 0.0741 0.01152 0.00408 -0.1009 0.5443 0.0793
-4.000 0.1015 0.01150 0.00396 -0.1003 0.5307 0.0806
-3.750 0.1287 0.01146 0.00384 -0.0998 0.5184 0.0817
-3.500 0.1558 0.01134 0.00367 -0.0993 0.5068 0.0830
-3.250 0.1831 0.01127 0.00355 -0.0988 0.4955 0.0841
-2.750 0.2380 0.01119 0.00335 -0.0978 0.4728 0.0864
-2.500 0.2653 0.01116 0.00327 -0.0973 0.4638 0.0876
-2.250 0.2933 0.01112 0.00319 -0.0969 0.4563 0.0890
-2.000 0.3209 0.01112 0.00313 -0.0965 0.4478 0.0902
-1.750 0.3484 0.01104 0.00303 -0.0960 0.4403 0.0919
-1.500 0.3762 0.01098 0.00296 -0.0956 0.4333 0.0930
-1.250 0.4036 0.01097 0.00290 -0.0951 0.4259 0.0942
-1.000 0.4314 0.01095 0.00286 -0.0947 0.4189 0.0956
-0.750 0.4590 0.01094 0.00283 -0.0943 0.4108 0.0972
-0.500 0.4864 0.01097 0.00281 -0.0938 0.4037 0.0989
-0.250 0.5142 0.01096 0.00279 -0.0934 0.3972 0.1013
0.000 0.5416 0.01096 0.00279 -0.0929 0.3899 0.1056
0.250 0.5689 0.01097 0.00279 -0.0925 0.3830 0.1130
0.750 0.6227 0.01085 0.00284 -0.0916 0.3671 0.1843
1.000 0.6500 0.01082 0.00290 -0.0912 0.3601 0.2189
1.250 0.6768 0.01084 0.00298 -0.0907 0.3523 0.2489
1.500 0.7037 0.01088 0.00306 -0.0902 0.3448 0.2753
1.750 0.7305 0.01096 0.00315 -0.0897 0.3359 0.2955
2.000 0.7572 0.01105 0.00326 -0.0892 0.3276 0.3135
2.250 0.7838 0.01114 0.00337 -0.0886 0.3194 0.3323
2.500 0.8102 0.01127 0.00349 -0.0881 0.3115 0.3470
2.750 0.8366 0.01139 0.00361 -0.0875 0.3024 0.3612
3.250 0.8889 0.01168 0.00390 -0.0864 0.2857 0.3898
3.500 0.9145 0.01185 0.00407 -0.0857 0.2778 0.4063
3.750 0.9404 0.01200 0.00423 -0.0851 0.2699 0.4211
4.000 0.9656 0.01221 0.00441 -0.0845 0.2622 0.4340
4.250 0.9914 0.01236 0.00458 -0.0838 0.2554 0.4464
4.500 1.0164 0.01257 0.00478 -0.0831 0.2484 0.4605
4.750 1.0415 0.01275 0.00498 -0.0825 0.2425 0.4764
5.000 1.0666 0.01292 0.00518 -0.0818 0.2367 0.4952
5.500 1.1155 0.01331 0.00563 -0.0802 0.2267 0.5296
6.000 1.1635 0.01365 0.00609 -0.0786 0.2173 0.5821
6.250 1.1831 0.01359 0.00636 -0.0770 0.2133 0.7131
6.750 1.2558 0.01380 0.00693 -0.0805 0.2047 1.0000
7.000 1.2788 0.01411 0.00720 -0.0796 0.2005 1.0000
7.250 1.3012 0.01444 0.00751 -0.0786 0.1968 1.0000
7.500 1.3249 0.01468 0.00777 -0.0777 0.1939 1.0000
7.750 1.3478 0.01496 0.00804 -0.0768 0.1902 1.0000
8.000 1.3696 0.01529 0.00836 -0.0757 0.1863 1.0000
8.250 1.3903 0.01567 0.00871 -0.0745 0.1825 1.0000
8.500 1.4122 0.01596 0.00902 -0.0734 0.1794 1.0000
8.750 1.4333 0.01628 0.00935 -0.0723 0.1753 1.0000
9.000 1.4527 0.01667 0.00972 -0.0709 0.1708 1.0000
9.250 1.4707 0.01708 0.01012 -0.0693 0.1668 1.0000
9.500 1.4889 0.01742 0.01048 -0.0677 0.1633 1.0000
9.750 1.5052 0.01781 0.01088 -0.0658 0.1594 1.0000
10.000 1.5196 0.01829 0.01136 -0.0637 0.1558 1.0000
10.250 1.5348 0.01876 0.01184 -0.0618 0.1527 1.0000
10.500 1.5505 0.01922 0.01233 -0.0600 0.1495 1.0000
10.750 1.5649 0.01975 0.01288 -0.0582 0.1461 1.0000
11.000 1.5771 0.02042 0.01355 -0.0562 0.1425 1.0000
11.250 1.5904 0.02106 0.01422 -0.0544 0.1394 1.0000
11.500 1.6036 0.02174 0.01493 -0.0527 0.1363 1.0000
11.750 1.6149 0.02256 0.01578 -0.0510 0.1329 1.0000
12.000 1.6244 0.02354 0.01677 -0.0493 0.1300 1.0000
12.250 1.6355 0.02448 0.01776 -0.0479 0.1276 1.0000
12.500 1.6462 0.02550 0.01883 -0.0466 0.1249 1.0000
12.750 1.6553 0.02670 0.02007 -0.0454 0.1222 1.0000
13.000 1.6624 0.02812 0.02152 -0.0442 0.1196 1.0000
13.250 1.6690 0.02966 0.02311 -0.0432 0.1172 1.0000
13.500 1.6775 0.03110 0.02461 -0.0423 0.1151 1.0000
13.750 1.6841 0.03276 0.02633 -0.0415 0.1127 1.0000
14.000 1.6886 0.03467 0.02829 -0.0409 0.1103 1.0000
14.250 1.6901 0.03691 0.03058 -0.0403 0.1080 1.0000
14.500 1.6926 0.03914 0.03287 -0.0398 0.1061 1.0000
14.750 1.6960 0.04132 0.03514 -0.0395 0.1042 1.0000
15.000 1.6972 0.04377 0.03766 -0.0392 0.1024 1.0000
15.250 1.6961 0.04655 0.04051 -0.0391 0.1005 1.0000
15.500 1.6925 0.04970 0.04373 -0.0392 0.0987 1.0000
15.750 1.6863 0.05326 0.04735 -0.0395 0.0971 1.0000
16.000 1.6843 0.05640 0.05059 -0.0398 0.0957 1.0000
16.250 1.6817 0.05968 0.05395 -0.0403 0.0940 1.0000
16.500 1.6773 0.06323 0.05759 -0.0408 0.0926 1.0000
16.750 1.6698 0.06723 0.06167 -0.0416 0.0907 1.0000
17.000 1.6597 0.07167 0.06617 -0.0426 0.0889 1.0000
17.250 1.6482 0.07635 0.07092 -0.0438 0.0873 1.0000
17.500 1.6436 0.08013 0.07480 -0.0446 0.0858 1.0000
17.750 1.6359 0.08443 0.07919 -0.0458 0.0841 1.0000
18.000 1.6263 0.08905 0.08388 -0.0472 0.0824 1.0000
18.250 1.6150 0.09399 0.08890 -0.0488 0.0808 1.0000
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