GOE 493 AIRFOIL (goe493-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 493 AIRFOIL (goe493-il) Reynolds number: 200,000 Max Cl/Cd: 75.69 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe493-il-200000.txt Download as CSV file: xf-goe493-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 493 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.750 -0.5903 0.08290 0.07897 -0.0776 1.0000 0.0365
-13.500 -0.6285 0.07395 0.06994 -0.0822 1.0000 0.0357
-13.250 -0.6700 0.06592 0.06178 -0.0862 1.0000 0.0349
-13.000 -0.7051 0.06034 0.05607 -0.0879 1.0000 0.0346
-12.750 -0.7402 0.05594 0.05156 -0.0878 1.0000 0.0344
-12.500 -0.7731 0.05269 0.04819 -0.0862 1.0000 0.0342
-12.250 -0.8067 0.05004 0.04542 -0.0834 1.0000 0.0339
-12.000 -0.8416 0.04799 0.04325 -0.0792 1.0000 0.0336
-11.750 -0.8766 0.04668 0.04183 -0.0733 1.0000 0.0335
-11.500 -0.8950 0.04516 0.04017 -0.0691 0.9993 0.0337
-11.250 -0.8825 0.04230 0.03700 -0.0712 0.9943 0.0346
-11.000 -0.8708 0.03963 0.03397 -0.0722 0.9888 0.0356
-10.750 -0.8526 0.03724 0.03110 -0.0737 0.9840 0.0367
-10.500 -0.8362 0.03463 0.02824 -0.0739 0.9791 0.0375
-10.250 -0.8130 0.03290 0.02650 -0.0747 0.9748 0.0390
-10.000 -0.7841 0.03138 0.02483 -0.0764 0.9715 0.0406
-9.750 -0.7631 0.03011 0.02336 -0.0763 0.9664 0.0424
-9.500 -0.7402 0.02860 0.02166 -0.0766 0.9614 0.0447
-9.250 -0.7095 0.02744 0.02052 -0.0782 0.9582 0.0475
-9.000 -0.6816 0.02643 0.01935 -0.0790 0.9545 0.0507
-8.750 -0.6638 0.02525 0.01816 -0.0780 0.9480 0.0540
-8.500 -0.6324 0.02446 0.01728 -0.0794 0.9444 0.0596
-8.250 -0.5983 0.02348 0.01632 -0.0814 0.9420 0.0671
-8.000 -0.5841 0.02278 0.01560 -0.0794 0.9343 0.0739
-7.750 -0.5540 0.02214 0.01494 -0.0804 0.9302 0.0854
-7.500 -0.5178 0.02154 0.01431 -0.0825 0.9276 0.0994
-7.250 -0.4956 0.02115 0.01388 -0.0818 0.9217 0.1110
-7.000 -0.4689 0.02082 0.01346 -0.0819 0.9162 0.1228
-6.750 -0.4330 0.02041 0.01299 -0.0839 0.9133 0.1359
-6.500 -0.3948 0.01989 0.01248 -0.0862 0.9114 0.1494
-6.250 -0.3795 0.01959 0.01221 -0.0841 0.9033 0.1581
-6.000 -0.3465 0.01913 0.01172 -0.0853 0.8995 0.1704
-5.750 -0.3083 0.01863 0.01121 -0.0875 0.8972 0.1844
-5.500 -0.2683 0.01807 0.01068 -0.0901 0.8956 0.2007
-5.250 -0.2533 0.01792 0.01050 -0.0877 0.8872 0.2133
-5.000 -0.2197 0.01734 0.01004 -0.0891 0.8838 0.2328
-4.750 -0.1821 0.01677 0.00956 -0.0911 0.8814 0.2599
-4.500 -0.1447 0.01616 0.00909 -0.0931 0.8795 0.2949
-4.250 -0.1299 0.01600 0.00904 -0.0907 0.8710 0.3254
-4.000 -0.0983 0.01557 0.00877 -0.0914 0.8670 0.3659
-3.750 -0.0618 0.01520 0.00847 -0.0930 0.8645 0.4078
-3.500 -0.0242 0.01488 0.00822 -0.0947 0.8625 0.4435
-3.250 -0.0114 0.01495 0.00833 -0.0918 0.8527 0.4658
-3.000 0.0238 0.01470 0.00809 -0.0930 0.8494 0.4931
-2.750 0.0613 0.01443 0.00783 -0.0946 0.8470 0.5185
-2.500 0.0772 0.01452 0.00793 -0.0922 0.8380 0.5364
-2.250 0.1105 0.01431 0.00771 -0.0930 0.8340 0.5573
-2.000 0.1472 0.01403 0.00746 -0.0944 0.8312 0.5775
-1.750 0.1646 0.01408 0.00754 -0.0923 0.8223 0.5942
-1.500 0.1969 0.01387 0.00736 -0.0929 0.8180 0.6139
-1.250 0.2325 0.01363 0.00713 -0.0941 0.8149 0.6348
-1.000 0.2496 0.01368 0.00724 -0.0918 0.8057 0.6519
-0.750 0.2823 0.01346 0.00705 -0.0925 0.8013 0.6715
-0.500 0.3092 0.01339 0.00701 -0.0921 0.7954 0.6901
-0.250 0.3336 0.01332 0.00700 -0.0912 0.7883 0.7088
0.000 0.3671 0.01311 0.00683 -0.0920 0.7841 0.7290
0.250 0.3871 0.01311 0.00691 -0.0902 0.7756 0.7497
0.500 0.4177 0.01290 0.00673 -0.0903 0.7696 0.7732
0.750 0.4414 0.01279 0.00668 -0.0891 0.7612 0.7958
1.000 0.4706 0.01255 0.00648 -0.0889 0.7539 0.8211
1.250 0.4946 0.01245 0.00646 -0.0877 0.7454 0.8479
1.500 0.5258 0.01231 0.00638 -0.0880 0.7386 0.8777
1.750 0.5634 0.01229 0.00641 -0.0897 0.7319 0.9085
2.000 0.6104 0.01231 0.00645 -0.0935 0.7244 0.9350
2.250 0.6632 0.01233 0.00643 -0.0986 0.7185 0.9551
2.500 0.7124 0.01242 0.00655 -0.1032 0.7100 0.9729
2.750 0.7650 0.01241 0.00649 -0.1083 0.7034 0.9865
3.000 0.8096 0.01249 0.00659 -0.1123 0.6939 1.0000
3.250 0.8274 0.01252 0.00655 -0.1107 0.6869 1.0000
3.500 0.8404 0.01265 0.00668 -0.1080 0.6781 1.0000
3.750 0.8644 0.01274 0.00671 -0.1073 0.6711 1.0000
4.000 0.8814 0.01289 0.00689 -0.1053 0.6620 1.0000
4.250 0.9053 0.01301 0.00698 -0.1045 0.6542 1.0000
4.500 0.9249 0.01316 0.00713 -0.1029 0.6449 1.0000
4.750 0.9465 0.01332 0.00728 -0.1016 0.6361 1.0000
5.000 0.9705 0.01340 0.00732 -0.1007 0.6257 1.0000
5.250 0.9870 0.01351 0.00745 -0.0984 0.6127 1.0000
5.500 1.0048 0.01361 0.00753 -0.0962 0.5988 1.0000
5.750 1.0230 0.01373 0.00765 -0.0942 0.5851 1.0000
6.000 1.0401 0.01385 0.00774 -0.0919 0.5700 1.0000
6.250 1.0552 0.01398 0.00785 -0.0893 0.5534 1.0000
6.500 1.0702 0.01414 0.00799 -0.0867 0.5369 1.0000
6.750 1.0846 0.01434 0.00818 -0.0840 0.5201 1.0000
7.000 1.0976 0.01456 0.00838 -0.0811 0.5025 1.0000
7.250 1.1085 0.01482 0.00859 -0.0778 0.4834 1.0000
7.500 1.1164 0.01511 0.00884 -0.0740 0.4645 1.0000
7.750 1.1233 0.01544 0.00917 -0.0700 0.4440 1.0000
8.000 1.1300 0.01586 0.00953 -0.0662 0.4222 1.0000
8.250 1.1362 0.01637 0.00998 -0.0624 0.3984 1.0000
8.500 1.1397 0.01703 0.01052 -0.0584 0.3722 1.0000
8.750 1.1408 0.01787 0.01122 -0.0542 0.3423 1.0000
9.000 1.1394 0.01891 0.01210 -0.0499 0.3072 1.0000
9.250 1.1306 0.02039 0.01332 -0.0448 0.2507 1.0000
9.500 1.1088 0.02283 0.01517 -0.0389 0.1660 1.0000
9.750 1.0923 0.02539 0.01733 -0.0341 0.1119 1.0000
10.000 1.0855 0.02753 0.01927 -0.0306 0.0882 1.0000
10.250 1.0832 0.02946 0.02114 -0.0279 0.0791 1.0000
10.500 1.0855 0.03116 0.02288 -0.0257 0.0733 1.0000
10.750 1.0825 0.03331 0.02501 -0.0233 0.0693 1.0000
11.000 1.0892 0.03482 0.02661 -0.0217 0.0661 1.0000
11.250 1.0945 0.03649 0.02833 -0.0202 0.0633 1.0000
11.500 1.0982 0.03834 0.03021 -0.0186 0.0608 1.0000
11.750 1.0995 0.04043 0.03225 -0.0169 0.0586 1.0000
12.000 1.1095 0.04187 0.03380 -0.0158 0.0569 1.0000
12.250 1.1188 0.04339 0.03539 -0.0147 0.0549 1.0000
12.500 1.1281 0.04493 0.03697 -0.0137 0.0530 1.0000
12.750 1.1379 0.04647 0.03848 -0.0126 0.0511 1.0000
13.000 1.1557 0.04760 0.03954 -0.0113 0.0492 1.0000
13.250 1.1666 0.04908 0.04117 -0.0105 0.0478 1.0000
13.500 1.1794 0.05050 0.04269 -0.0097 0.0463 1.0000
13.750 1.1932 0.05190 0.04416 -0.0088 0.0448 1.0000
14.000 1.2076 0.05331 0.04560 -0.0081 0.0435 1.0000
14.250 1.2423 0.05428 0.04648 -0.0077 0.0413 1.0000
14.500 1.2456 0.05634 0.04876 -0.0067 0.0405 1.0000
14.750 1.2527 0.05842 0.05104 -0.0059 0.0396 1.0000
15.000 1.2610 0.06061 0.05341 -0.0051 0.0387 1.0000
15.250 1.2681 0.06289 0.05585 -0.0044 0.0378 1.0000
15.500 1.2752 0.06518 0.05827 -0.0039 0.0369 1.0000
15.750 1.2803 0.06757 0.06077 -0.0034 0.0361 1.0000
16.000 1.1328 0.07472 0.06896 0.0002 0.0376 1.0000
16.250 1.1250 0.07834 0.07276 -0.0001 0.0370 1.0000
16.500 1.1155 0.08193 0.07653 -0.0006 0.0365 1.0000
16.750 1.0976 0.08562 0.08045 -0.0015 0.0362 1.0000
17.000 1.0800 0.08959 0.08462 -0.0028 0.0359 1.0000
17.250 1.0618 0.09395 0.08920 -0.0046 0.0356 1.0000
17.500 1.0369 0.09940 0.09490 -0.0073 0.0356 1.0000
17.750 1.1961 0.10354 0.09846 -0.0076 0.0336 1.0000
18.000 1.1749 0.11010 0.10525 -0.0102 0.0336 1.0000
18.250 1.1526 0.11717 0.11253 -0.0135 0.0337 1.0000
18.500 1.1298 0.12477 0.12032 -0.0174 0.0339 1.0000
18.750 1.1061 0.13301 0.12874 -0.0219 0.0341 1.0000
19.000 1.0856 0.14124 0.13710 -0.0263 0.0344 1.0000
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Polar data table (+)
Polar graphs
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