GOE 591 AIRFOIL (goe591-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 591 AIRFOIL (goe591-il) Reynolds number: 200,000 Max Cl/Cd: 76.91 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe591-il-200000-n5.txt Download as CSV file: xf-goe591-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 591 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2386 0.08576 0.08237 -0.0588 0.9780 0.0222
-8.500 -0.2288 0.08079 0.07741 -0.0640 0.9703 0.0223
-8.250 -0.2246 0.07357 0.07020 -0.0723 0.9601 0.0233
-8.000 -0.2165 0.06569 0.06232 -0.0831 0.9486 0.0243
-7.750 -0.1996 0.06300 0.05960 -0.0867 0.9376 0.0249
-7.500 -0.1830 0.05833 0.05486 -0.0929 0.9266 0.0255
-7.250 -0.1676 0.05180 0.04818 -0.1005 0.9153 0.0260
-7.000 -0.1519 0.04543 0.04160 -0.1063 0.9037 0.0274
-6.750 -0.1531 0.03286 0.02825 -0.1114 0.8895 0.0293
-6.500 -0.1427 0.02704 0.02154 -0.1116 0.8782 0.0306
-6.250 -0.1223 0.02442 0.01849 -0.1116 0.8695 0.0320
-6.000 -0.0969 0.02332 0.01722 -0.1117 0.8610 0.0333
-5.750 -0.0732 0.02191 0.01551 -0.1114 0.8518 0.0344
-5.250 -0.0226 0.01958 0.01257 -0.1108 0.8345 0.0372
-5.000 0.0036 0.01851 0.01118 -0.1105 0.8265 0.0384
-4.750 0.0293 0.01760 0.01001 -0.1100 0.8178 0.0391
-4.500 0.0555 0.01685 0.00905 -0.1096 0.8097 0.0397
-4.250 0.0812 0.01598 0.00804 -0.1092 0.8015 0.0411
-4.000 0.1069 0.01546 0.00745 -0.1087 0.7932 0.0426
-3.750 0.1332 0.01498 0.00688 -0.1083 0.7850 0.0438
-3.500 0.1588 0.01454 0.00635 -0.1078 0.7765 0.0449
-3.250 0.1851 0.01415 0.00586 -0.1073 0.7684 0.0462
-3.000 0.2105 0.01381 0.00545 -0.1067 0.7594 0.0477
-2.750 0.2369 0.01352 0.00505 -0.1063 0.7513 0.0492
-2.500 0.2621 0.01324 0.00476 -0.1057 0.7418 0.0519
-2.250 0.2883 0.01305 0.00453 -0.1053 0.7333 0.0563
-2.000 0.3141 0.01285 0.00429 -0.1047 0.7239 0.0623
-1.750 0.3399 0.01268 0.00408 -0.1042 0.7144 0.0731
-1.500 0.3660 0.01250 0.00387 -0.1037 0.7054 0.0884
-1.250 0.3913 0.01234 0.00373 -0.1032 0.6952 0.1047
-1.000 0.4169 0.01220 0.00363 -0.1027 0.6854 0.1276
-0.750 0.4425 0.01208 0.00356 -0.1022 0.6755 0.1620
-0.500 0.4677 0.01196 0.00352 -0.1017 0.6649 0.2055
-0.250 0.4924 0.01177 0.00348 -0.1011 0.6548 0.2610
0.000 0.5139 0.01124 0.00348 -0.1001 0.6448 0.4430
0.500 0.6148 0.01022 0.00355 -0.1090 0.6215 1.0000
0.750 0.6380 0.01034 0.00354 -0.1080 0.6110 1.0000
1.000 0.6612 0.01048 0.00354 -0.1070 0.6002 1.0000
1.250 0.6843 0.01061 0.00358 -0.1060 0.5893 1.0000
1.500 0.7075 0.01076 0.00362 -0.1050 0.5788 1.0000
1.750 0.7306 0.01092 0.00367 -0.1040 0.5685 1.0000
2.000 0.7536 0.01108 0.00374 -0.1030 0.5570 1.0000
2.250 0.7765 0.01125 0.00382 -0.1019 0.5454 1.0000
2.500 0.7994 0.01143 0.00391 -0.1009 0.5343 1.0000
2.750 0.8224 0.01162 0.00402 -0.1000 0.5238 1.0000
3.000 0.8457 0.01180 0.00415 -0.0991 0.5139 1.0000
3.250 0.8690 0.01200 0.00429 -0.0982 0.5053 1.0000
3.500 0.8924 0.01220 0.00445 -0.0973 0.4962 1.0000
3.750 0.9158 0.01240 0.00461 -0.0965 0.4882 1.0000
4.000 0.9393 0.01261 0.00479 -0.0957 0.4803 1.0000
4.250 0.9626 0.01282 0.00498 -0.0949 0.4724 1.0000
4.500 0.9855 0.01305 0.00518 -0.0940 0.4636 1.0000
4.750 1.0082 0.01328 0.00540 -0.0931 0.4538 1.0000
5.000 1.0305 0.01353 0.00561 -0.0921 0.4449 1.0000
5.250 1.0527 0.01376 0.00586 -0.0911 0.4350 1.0000
5.500 1.0749 0.01401 0.00611 -0.0901 0.4258 1.0000
5.750 1.0963 0.01429 0.00636 -0.0890 0.4167 1.0000
6.000 1.1182 0.01454 0.00665 -0.0880 0.4070 1.0000
6.250 1.1394 0.01483 0.00694 -0.0869 0.3984 1.0000
6.500 1.1603 0.01511 0.00724 -0.0857 0.3885 1.0000
6.750 1.1810 0.01540 0.00756 -0.0845 0.3786 1.0000
7.000 1.2008 0.01572 0.00790 -0.0832 0.3697 1.0000
7.250 1.2212 0.01602 0.00826 -0.0820 0.3604 1.0000
7.500 1.2403 0.01636 0.00863 -0.0806 0.3505 1.0000
7.750 1.2571 0.01674 0.00901 -0.0788 0.3374 1.0000
8.000 1.2714 0.01715 0.00942 -0.0765 0.3210 1.0000
8.250 1.2834 0.01762 0.00986 -0.0739 0.3036 1.0000
8.500 1.2944 0.01817 0.01036 -0.0713 0.2861 1.0000
8.750 1.3043 0.01880 0.01094 -0.0685 0.2686 1.0000
9.000 1.3138 0.01950 0.01159 -0.0659 0.2516 1.0000
9.250 1.3229 0.02027 0.01233 -0.0633 0.2332 1.0000
9.500 1.3298 0.02120 0.01318 -0.0605 0.2126 1.0000
9.750 1.3357 0.02223 0.01413 -0.0578 0.1927 1.0000
10.000 1.3423 0.02329 0.01514 -0.0554 0.1708 1.0000
10.250 1.3471 0.02452 0.01629 -0.0529 0.1508 1.0000
10.500 1.3482 0.02606 0.01771 -0.0503 0.1291 1.0000
10.750 1.3495 0.02768 0.01926 -0.0478 0.1121 1.0000
11.250 1.3355 0.03251 0.02373 -0.0426 0.0508 1.0000
11.500 1.3271 0.03528 0.02642 -0.0403 0.0275 1.0000
11.750 1.3246 0.03770 0.02884 -0.0387 0.0222 1.0000
12.000 1.3249 0.03997 0.03118 -0.0374 0.0201 1.0000
12.250 1.3238 0.04246 0.03378 -0.0363 0.0183 1.0000
12.500 1.3230 0.04504 0.03648 -0.0354 0.0173 1.0000
12.750 1.3239 0.04754 0.03912 -0.0347 0.0165 1.0000
13.000 1.3239 0.05022 0.04195 -0.0342 0.0158 1.0000
13.250 1.3223 0.05319 0.04507 -0.0338 0.0152 1.0000
13.500 1.3197 0.05641 0.04843 -0.0337 0.0148 1.0000
13.750 1.3160 0.05987 0.05204 -0.0337 0.0144 1.0000
14.000 1.3110 0.06362 0.05596 -0.0340 0.0141 1.0000
14.250 1.3046 0.06770 0.06018 -0.0345 0.0138 1.0000
14.500 1.2969 0.07209 0.06471 -0.0353 0.0135 1.0000
14.750 1.2860 0.07706 0.06982 -0.0364 0.0132 1.0000
15.000 1.2756 0.08213 0.07502 -0.0376 0.0129 1.0000
15.250 1.2663 0.08711 0.08013 -0.0390 0.0128 1.0000
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Polar data table (+)
Polar graphs
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