GOE 533 AIRFOIL (goe533-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 533 AIRFOIL (goe533-il) Reynolds number: 500,000 Max Cl/Cd: 106.25 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe533-il-500000.txt Download as CSV file: xf-goe533-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 533 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2972 0.12664 0.12418 -0.0334 1.0000 0.0284
-12.000 -0.2927 0.12353 0.12108 -0.0344 1.0000 0.0294
-11.750 -0.3150 0.11568 0.11325 -0.0415 1.0000 0.0309
-11.500 -0.3058 0.11308 0.11067 -0.0404 1.0000 0.0312
-11.250 -0.2971 0.11090 0.10851 -0.0400 1.0000 0.0314
-11.000 -0.2893 0.10866 0.10628 -0.0398 1.0000 0.0317
-10.750 -0.2825 0.10638 0.10402 -0.0398 1.0000 0.0321
-10.500 -0.2782 0.10379 0.10147 -0.0400 1.0000 0.0325
-10.250 -0.2186 0.08679 0.08469 -0.0509 0.9956 0.0361
-10.000 -0.1991 0.08391 0.08181 -0.0521 0.9878 0.0365
-9.750 -0.1797 0.08082 0.07871 -0.0544 0.9792 0.0369
-9.500 -0.1592 0.07689 0.07477 -0.0584 0.9694 0.0377
-9.250 -0.2810 0.08334 0.08115 -0.0507 0.9953 0.0367
-9.000 -0.2602 0.08049 0.07831 -0.0539 0.9857 0.0372
-8.750 -0.2415 0.07675 0.07456 -0.0586 0.9731 0.0380
-8.500 -0.2735 0.04832 0.04567 -0.1035 0.9361 0.0421
-8.250 -0.2409 0.04601 0.04334 -0.1066 0.9103 0.0425
-8.000 -0.2212 0.04397 0.04114 -0.1083 0.8703 0.0429
-7.750 -0.2092 0.04234 0.03928 -0.1082 0.8262 0.0434
-7.500 -0.1998 0.04031 0.03698 -0.1080 0.7895 0.0442
-7.250 -0.2084 0.03422 0.02993 -0.1094 0.7628 0.0489
-7.000 -0.1883 0.03248 0.02817 -0.1091 0.7427 0.0495
-6.750 -0.1681 0.03112 0.02670 -0.1088 0.7264 0.0501
-6.500 -0.1474 0.02982 0.02525 -0.1086 0.7136 0.0511
-6.250 -0.1356 0.02281 0.01686 -0.1077 0.7042 0.0419
-6.000 -0.1122 0.02058 0.01453 -0.1074 0.6949 0.0408
-5.750 -0.0880 0.01898 0.01269 -0.1071 0.6860 0.0404
-5.500 -0.0627 0.01772 0.01120 -0.1067 0.6781 0.0400
-5.250 -0.0368 0.01670 0.01001 -0.1064 0.6705 0.0400
-5.000 -0.0105 0.01590 0.00903 -0.1060 0.6635 0.0401
-4.750 0.0163 0.01518 0.00821 -0.1057 0.6568 0.0403
-4.500 0.0432 0.01467 0.00756 -0.1054 0.6503 0.0408
-4.250 0.0705 0.01432 0.00710 -0.1051 0.6444 0.0413
-4.000 0.0980 0.01396 0.00667 -0.1049 0.6383 0.0417
-3.750 0.1241 0.01312 0.00578 -0.1045 0.6326 0.0422
-3.500 0.1506 0.01258 0.00523 -0.1042 0.6271 0.0428
-3.250 0.1777 0.01218 0.00483 -0.1040 0.6214 0.0436
-3.000 0.2049 0.01189 0.00451 -0.1038 0.6159 0.0445
-2.750 0.2322 0.01166 0.00423 -0.1036 0.6108 0.0455
-2.500 0.2599 0.01141 0.00398 -0.1034 0.6052 0.0467
-2.250 0.2876 0.01124 0.00377 -0.1032 0.5994 0.0480
-2.000 0.3148 0.01098 0.00345 -0.1030 0.5939 0.0497
-1.750 0.3426 0.01073 0.00322 -0.1029 0.5883 0.0519
-1.500 0.3705 0.01058 0.00305 -0.1027 0.5826 0.0545
-1.250 0.3982 0.01047 0.00287 -0.1026 0.5770 0.0588
-1.000 0.4262 0.01025 0.00274 -0.1025 0.5711 0.0728
-0.750 0.4521 0.00939 0.00260 -0.1026 0.5649 0.2901
-0.500 0.4779 0.00897 0.00265 -0.1024 0.5588 0.4768
-0.250 0.5055 0.00886 0.00267 -0.1022 0.5520 0.5207
0.000 0.5326 0.00881 0.00268 -0.1019 0.5450 0.5568
0.250 0.5598 0.00877 0.00273 -0.1016 0.5375 0.5969
0.500 0.5868 0.00878 0.00277 -0.1012 0.5289 0.6297
0.750 0.6139 0.00880 0.00283 -0.1008 0.5207 0.6585
1.000 0.6406 0.00884 0.00289 -0.1004 0.5124 0.6902
1.250 0.6673 0.00887 0.00295 -0.1000 0.5044 0.7171
1.500 0.6940 0.00890 0.00298 -0.0996 0.4957 0.7340
1.750 0.7209 0.00893 0.00302 -0.0993 0.4876 0.7493
2.000 0.7473 0.00897 0.00306 -0.0988 0.4792 0.7668
2.250 0.7734 0.00898 0.00312 -0.0984 0.4710 0.7881
2.500 0.7982 0.00899 0.00318 -0.0976 0.4620 0.8186
2.750 0.8239 0.00879 0.00324 -0.0968 0.4534 0.9158
3.000 0.8603 0.00895 0.00331 -0.0987 0.4443 1.0000
3.250 0.8879 0.00908 0.00341 -0.0986 0.4364 1.0000
3.500 0.9143 0.00928 0.00352 -0.0984 0.4287 1.0000
3.750 0.9415 0.00942 0.00365 -0.0983 0.4219 1.0000
4.000 0.9680 0.00961 0.00378 -0.0980 0.4151 1.0000
4.250 0.9944 0.00980 0.00393 -0.0977 0.4086 1.0000
4.500 1.0210 0.00996 0.00407 -0.0975 0.4018 1.0000
4.750 1.0467 0.01020 0.00424 -0.0971 0.3955 1.0000
5.000 1.0734 0.01034 0.00440 -0.0969 0.3896 1.0000
5.250 1.0993 0.01054 0.00458 -0.0966 0.3834 1.0000
5.500 1.1246 0.01078 0.00477 -0.0962 0.3780 1.0000
5.750 1.1510 0.01093 0.00495 -0.0959 0.3722 1.0000
6.000 1.1760 0.01116 0.00515 -0.0955 0.3655 1.0000
6.250 1.2014 0.01136 0.00535 -0.0951 0.3591 1.0000
6.500 1.2267 0.01156 0.00555 -0.0947 0.3528 1.0000
7.000 1.2761 0.01201 0.00600 -0.0937 0.3404 1.0000
7.250 1.3001 0.01226 0.00624 -0.0931 0.3337 1.0000
7.500 1.3242 0.01250 0.00650 -0.0925 0.3279 1.0000
7.750 1.3484 0.01272 0.00674 -0.0920 0.3214 1.0000
8.000 1.3706 0.01304 0.00703 -0.0911 0.3145 1.0000
8.250 1.3947 0.01324 0.00729 -0.0906 0.3070 1.0000
8.500 1.4158 0.01359 0.00760 -0.0895 0.2985 1.0000
8.750 1.4384 0.01385 0.00789 -0.0888 0.2891 1.0000
9.000 1.4591 0.01419 0.00823 -0.0877 0.2801 1.0000
9.250 1.4786 0.01457 0.00860 -0.0864 0.2697 1.0000
9.500 1.4980 0.01494 0.00897 -0.0852 0.2582 1.0000
9.750 1.5140 0.01539 0.00940 -0.0834 0.2452 1.0000
10.000 1.5266 0.01593 0.00989 -0.0810 0.2309 1.0000
10.250 1.5374 0.01655 0.01046 -0.0784 0.2170 1.0000
10.500 1.5470 0.01725 0.01111 -0.0758 0.2049 1.0000
10.750 1.5551 0.01805 0.01186 -0.0731 0.1943 1.0000
11.000 1.5646 0.01882 0.01263 -0.0708 0.1860 1.0000
11.250 1.5731 0.01968 0.01349 -0.0684 0.1792 1.0000
11.500 1.5820 0.02055 0.01439 -0.0663 0.1727 1.0000
11.750 1.5879 0.02165 0.01549 -0.0640 0.1660 1.0000
12.000 1.5963 0.02268 0.01655 -0.0621 0.1586 1.0000
12.250 1.6009 0.02401 0.01790 -0.0601 0.1518 1.0000
12.500 1.6082 0.02525 0.01918 -0.0585 0.1428 1.0000
12.750 1.6112 0.02690 0.02081 -0.0568 0.1291 1.0000
13.000 1.6043 0.02946 0.02325 -0.0549 0.1029 1.0000
13.250 1.5900 0.03290 0.02658 -0.0532 0.0860 1.0000
13.500 1.5822 0.03602 0.02970 -0.0521 0.0789 1.0000
13.750 1.5765 0.03910 0.03283 -0.0514 0.0748 1.0000
14.000 1.5700 0.04236 0.03615 -0.0509 0.0715 1.0000
14.250 1.5692 0.04511 0.03900 -0.0505 0.0693 1.0000
14.500 1.5652 0.04827 0.04223 -0.0503 0.0671 1.0000
14.750 1.5584 0.05184 0.04587 -0.0502 0.0650 1.0000
15.000 1.5495 0.05577 0.04987 -0.0504 0.0630 1.0000
15.250 1.5460 0.05918 0.05338 -0.0506 0.0614 1.0000
15.500 1.5448 0.06239 0.05669 -0.0509 0.0597 1.0000
15.750 1.5407 0.06607 0.06046 -0.0514 0.0578 1.0000
16.000 1.5343 0.07015 0.06461 -0.0521 0.0563 1.0000
16.250 1.5241 0.07487 0.06940 -0.0531 0.0544 1.0000
16.500 1.5201 0.07886 0.07348 -0.0541 0.0528 1.0000
16.750 1.5202 0.08227 0.07700 -0.0549 0.0508 1.0000
17.000 1.5159 0.08642 0.08122 -0.0560 0.0489 1.0000
17.250 1.5074 0.09126 0.08612 -0.0575 0.0470 1.0000
17.500 1.5022 0.09569 0.09064 -0.0589 0.0451 1.0000
17.750 1.5004 0.09962 0.09466 -0.0602 0.0425 1.0000
18.000 1.4925 0.10458 0.09966 -0.0619 0.0403 1.0000
18.250 1.4879 0.10905 0.10422 -0.0636 0.0378 1.0000
18.500 1.4822 0.11378 0.10901 -0.0654 0.0351 1.0000
18.750 1.4729 0.11915 0.11442 -0.0676 0.0332 1.0000
19.000 1.4691 0.12359 0.11893 -0.0695 0.0308 1.0000
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Polar data table (+)
Polar graphs
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