GOE 553 AIRFOIL (goe553-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GOE 553 AIRFOIL (goe553-il) Reynolds number: 500,000 Max Cl/Cd: 105.51 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe553-il-500000.txt Download as CSV file: xf-goe553-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 553 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.3046 0.13013 0.12765 -0.0311 1.0000 0.0284
-12.250 -0.3212 0.12330 0.12083 -0.0370 1.0000 0.0300
-12.000 -0.3166 0.11961 0.11716 -0.0372 1.0000 0.0302
-11.750 -0.3056 0.11763 0.11519 -0.0366 1.0000 0.0305
-11.500 -0.2965 0.11540 0.11297 -0.0364 1.0000 0.0308
-11.250 -0.2897 0.11294 0.11053 -0.0367 1.0000 0.0312
-11.000 -0.2848 0.11021 0.10783 -0.0372 1.0000 0.0316
-10.750 -0.2308 0.09534 0.09321 -0.0453 1.0000 0.0349
-10.500 -0.2241 0.09328 0.09118 -0.0439 1.0000 0.0352
-10.250 -0.2083 0.09072 0.08862 -0.0448 0.9983 0.0356
-10.000 -0.1916 0.08733 0.08523 -0.0473 0.9911 0.0361
-9.750 -0.1773 0.08335 0.08125 -0.0505 0.9820 0.0369
-9.500 -0.1656 0.07833 0.07622 -0.0549 0.9705 0.0383
-9.000 -0.2624 0.08264 0.08047 -0.0494 0.9903 0.0374
-8.750 -0.2935 0.06126 0.05907 -0.0769 0.9643 0.0406
-8.500 -0.2578 0.06111 0.05892 -0.0783 0.9524 0.0410
-8.250 -0.2186 0.05611 0.05385 -0.0898 0.9303 0.0417
-8.000 -0.1991 0.04809 0.04551 -0.1045 0.8850 0.0427
-7.750 -0.2362 0.03748 0.03382 -0.1104 0.8337 0.0471
-7.500 -0.2178 0.03587 0.03213 -0.1098 0.7984 0.0475
-7.250 -0.2006 0.03459 0.03069 -0.1091 0.7682 0.0481
-7.000 -0.1826 0.03324 0.02918 -0.1087 0.7450 0.0488
-6.750 -0.1644 0.03166 0.02738 -0.1084 0.7274 0.0501
-6.500 -0.1515 0.02831 0.02336 -0.1084 0.7143 0.0549
-6.250 -0.1370 0.02113 0.01496 -0.1071 0.7044 0.0404
-6.000 -0.1123 0.01982 0.01349 -0.1067 0.6942 0.0400
-5.750 -0.0876 0.01844 0.01191 -0.1063 0.6849 0.0399
-5.500 -0.0619 0.01751 0.01078 -0.1060 0.6766 0.0400
-5.250 -0.0357 0.01680 0.00990 -0.1056 0.6685 0.0402
-5.000 -0.0102 0.01558 0.00853 -0.1052 0.6615 0.0407
-4.750 0.0161 0.01472 0.00765 -0.1050 0.6545 0.0413
-4.500 0.0426 0.01417 0.00702 -0.1046 0.6479 0.0418
-4.250 0.0694 0.01367 0.00648 -0.1043 0.6419 0.0423
-4.000 0.0964 0.01323 0.00601 -0.1040 0.6357 0.0428
-3.750 0.1233 0.01287 0.00558 -0.1037 0.6299 0.0434
-3.500 0.1504 0.01252 0.00520 -0.1034 0.6242 0.0441
-3.250 0.1776 0.01219 0.00485 -0.1032 0.6183 0.0449
-3.000 0.2050 0.01199 0.00457 -0.1029 0.6129 0.0459
-2.750 0.2322 0.01172 0.00427 -0.1026 0.6076 0.0468
-2.500 0.2591 0.01129 0.00385 -0.1024 0.6018 0.0482
-2.250 0.2864 0.01107 0.00360 -0.1022 0.5959 0.0497
-2.000 0.3140 0.01091 0.00340 -0.1020 0.5904 0.0514
-1.750 0.3420 0.01074 0.00322 -0.1018 0.5846 0.0533
-1.500 0.3696 0.01054 0.00299 -0.1016 0.5788 0.0566
-1.250 0.3973 0.01044 0.00285 -0.1014 0.5732 0.0619
-1.000 0.4249 0.01014 0.00273 -0.1013 0.5668 0.0961
-0.750 0.4501 0.00926 0.00257 -0.1013 0.5605 0.3314
-0.500 0.4762 0.00892 0.00265 -0.1011 0.5543 0.4862
-0.250 0.5036 0.00885 0.00270 -0.1008 0.5472 0.5361
0.000 0.5306 0.00889 0.00272 -0.1004 0.5399 0.5659
0.250 0.5582 0.00886 0.00275 -0.1001 0.5314 0.5898
0.500 0.5852 0.00892 0.00276 -0.0998 0.5232 0.6113
0.750 0.6126 0.00891 0.00280 -0.0995 0.5144 0.6322
1.000 0.6390 0.00895 0.00285 -0.0990 0.5065 0.6578
1.250 0.6662 0.00896 0.00291 -0.0987 0.4977 0.6801
1.500 0.6927 0.00902 0.00295 -0.0982 0.4893 0.6965
1.750 0.7198 0.00904 0.00300 -0.0979 0.4805 0.7118
2.000 0.7461 0.00910 0.00305 -0.0975 0.4723 0.7294
2.250 0.7726 0.00913 0.00312 -0.0971 0.4631 0.7506
2.500 0.7979 0.00915 0.00320 -0.0965 0.4543 0.7797
2.750 0.8216 0.00908 0.00327 -0.0954 0.4455 0.8315
3.000 0.8598 0.00897 0.00334 -0.0975 0.4365 1.0000
3.250 0.8867 0.00914 0.00343 -0.0973 0.4283 1.0000
3.500 0.9135 0.00932 0.00355 -0.0971 0.4210 1.0000
3.750 0.9403 0.00948 0.00367 -0.0969 0.4138 1.0000
4.000 0.9664 0.00969 0.00381 -0.0965 0.4072 1.0000
4.250 0.9933 0.00984 0.00395 -0.0963 0.4004 1.0000
4.500 1.0191 0.01005 0.00410 -0.0959 0.3938 1.0000
4.750 1.0455 0.01022 0.00426 -0.0957 0.3878 1.0000
5.000 1.0717 0.01041 0.00443 -0.0953 0.3814 1.0000
5.250 1.0967 0.01066 0.00462 -0.0949 0.3754 1.0000
5.500 1.1234 0.01080 0.00479 -0.0946 0.3703 1.0000
5.750 1.1490 0.01100 0.00498 -0.0943 0.3648 1.0000
6.000 1.1737 0.01127 0.00520 -0.0937 0.3595 1.0000
6.250 1.1999 0.01143 0.00540 -0.0934 0.3547 1.0000
6.500 1.2252 0.01163 0.00561 -0.0930 0.3493 1.0000
6.750 1.2492 0.01191 0.00585 -0.0924 0.3438 1.0000
7.000 1.2746 0.01208 0.00606 -0.0920 0.3374 1.0000
7.250 1.2983 0.01233 0.00629 -0.0914 0.3301 1.0000
7.500 1.3224 0.01256 0.00654 -0.0908 0.3234 1.0000
7.750 1.3462 0.01280 0.00678 -0.0902 0.3161 1.0000
8.000 1.3689 0.01309 0.00706 -0.0894 0.3097 1.0000
8.250 1.3925 0.01332 0.00733 -0.0887 0.3020 1.0000
8.500 1.4140 0.01364 0.00763 -0.0877 0.2938 1.0000
8.750 1.4360 0.01393 0.00793 -0.0869 0.2841 1.0000
9.000 1.4569 0.01425 0.00826 -0.0858 0.2743 1.0000
9.250 1.4759 0.01466 0.00863 -0.0845 0.2636 1.0000
9.500 1.4946 0.01505 0.00902 -0.0831 0.2518 1.0000
9.750 1.5114 0.01548 0.00944 -0.0814 0.2398 1.0000
10.000 1.5248 0.01599 0.00992 -0.0792 0.2276 1.0000
10.250 1.5366 0.01657 0.01046 -0.0767 0.2166 1.0000
10.750 1.5589 0.01785 0.01170 -0.0720 0.1984 1.0000
11.000 1.5673 0.01865 0.01248 -0.0694 0.1902 1.0000
11.250 1.5766 0.01945 0.01328 -0.0672 0.1829 1.0000
11.500 1.5839 0.02039 0.01422 -0.0648 0.1765 1.0000
11.750 1.5939 0.02125 0.01512 -0.0628 0.1708 1.0000
12.000 1.5994 0.02240 0.01629 -0.0606 0.1656 1.0000
12.250 1.6090 0.02339 0.01734 -0.0590 0.1607 1.0000
12.500 1.6161 0.02461 0.01860 -0.0573 0.1548 1.0000
12.750 1.6192 0.02617 0.02018 -0.0555 0.1492 1.0000
13.000 1.6286 0.02740 0.02147 -0.0544 0.1412 1.0000
13.250 1.6321 0.02913 0.02323 -0.0531 0.1316 1.0000
13.750 1.6130 0.03536 0.02924 -0.0504 0.0883 1.0000
14.000 1.6001 0.03912 0.03297 -0.0496 0.0792 1.0000
14.250 1.5916 0.04258 0.03647 -0.0490 0.0743 1.0000
14.500 1.5811 0.04637 0.04031 -0.0487 0.0705 1.0000
14.750 1.5771 0.04954 0.04358 -0.0485 0.0678 1.0000
15.000 1.5703 0.05314 0.04726 -0.0485 0.0651 1.0000
15.250 1.5603 0.05724 0.05142 -0.0488 0.0628 1.0000
15.500 1.5494 0.06160 0.05585 -0.0492 0.0607 1.0000
15.750 1.5478 0.06493 0.05929 -0.0496 0.0588 1.0000
16.000 1.5424 0.06881 0.06326 -0.0503 0.0569 1.0000
16.250 1.5342 0.07319 0.06772 -0.0512 0.0550 1.0000
16.500 1.5227 0.07818 0.07277 -0.0523 0.0532 1.0000
16.750 1.5169 0.08244 0.07713 -0.0534 0.0517 1.0000
17.000 1.5149 0.08621 0.08100 -0.0544 0.0498 1.0000
17.250 1.5085 0.09071 0.08557 -0.0557 0.0481 1.0000
17.500 1.4989 0.09578 0.09070 -0.0574 0.0464 1.0000
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