GOE 533 AIRFOIL (goe533-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 533 AIRFOIL (goe533-il) Reynolds number: 1,000,000 Max Cl/Cd: 131.08 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe533-il-1000000.txt Download as CSV file: xf-goe533-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.1324 0.06918 0.06740 -0.0763 0.9189 0.0274
-9.750 -0.4030 0.04223 0.04017 -0.1013 0.9614 0.0268
-9.500 -0.3719 0.03822 0.03599 -0.1098 0.9416 0.0271
-9.250 -0.3527 0.03557 0.03311 -0.1131 0.9030 0.0273
-9.000 -0.3440 0.03385 0.03110 -0.1126 0.8556 0.0275
-8.750 -0.3350 0.03230 0.02927 -0.1116 0.8094 0.0277
-8.500 -0.3232 0.03095 0.02764 -0.1106 0.7685 0.0280
-8.250 -0.3044 0.03048 0.02701 -0.1099 0.7366 0.0286
-8.000 -0.3219 0.01949 0.01444 -0.1089 0.7185 0.0268
-7.750 -0.3008 0.01795 0.01269 -0.1084 0.7007 0.0271
-7.500 -0.2766 0.01716 0.01176 -0.1080 0.6865 0.0274
-7.250 -0.2515 0.01658 0.01109 -0.1077 0.6753 0.0277
-6.750 -0.1999 0.01552 0.00984 -0.1071 0.6574 0.0283
-6.500 -0.1738 0.01507 0.00930 -0.1068 0.6495 0.0288
-6.250 -0.1473 0.01455 0.00868 -0.1066 0.6430 0.0292
-6.000 -0.1209 0.01392 0.00795 -0.1063 0.6365 0.0295
-5.750 -0.0945 0.01343 0.00734 -0.1060 0.6301 0.0298
-5.500 -0.0673 0.01294 0.00679 -0.1058 0.6251 0.0301
-5.250 -0.0401 0.01254 0.00631 -0.1056 0.6196 0.0304
-5.000 -0.0130 0.01222 0.00592 -0.1053 0.6144 0.0307
-4.750 0.0146 0.01196 0.00560 -0.1051 0.6097 0.0309
-4.500 0.0407 0.01115 0.00477 -0.1049 0.6051 0.0315
-4.250 0.0677 0.01077 0.00437 -0.1047 0.6002 0.0321
-4.000 0.0950 0.01054 0.00412 -0.1045 0.5954 0.0327
-3.750 0.1228 0.01029 0.00386 -0.1044 0.5914 0.0332
-3.500 0.1508 0.01005 0.00360 -0.1043 0.5867 0.0338
-3.250 0.1785 0.00985 0.00336 -0.1041 0.5816 0.0343
-3.000 0.2062 0.00970 0.00316 -0.1039 0.5764 0.0349
-2.750 0.2346 0.00951 0.00297 -0.1039 0.5723 0.0355
-2.500 0.2628 0.00938 0.00281 -0.1038 0.5673 0.0359
-2.250 0.2903 0.00910 0.00249 -0.1036 0.5621 0.0371
-2.000 0.3185 0.00896 0.00234 -0.1036 0.5571 0.0383
-1.750 0.3469 0.00885 0.00223 -0.1035 0.5514 0.0399
-1.500 0.3750 0.00878 0.00212 -0.1034 0.5454 0.0411
-1.250 0.4032 0.00867 0.00198 -0.1033 0.5397 0.0431
-1.000 0.4315 0.00857 0.00188 -0.1033 0.5324 0.0461
-0.750 0.4594 0.00851 0.00179 -0.1031 0.5249 0.0519
-0.500 0.4872 0.00821 0.00171 -0.1031 0.5171 0.1203
-0.250 0.5134 0.00769 0.00164 -0.1031 0.5089 0.2946
0.000 0.5404 0.00730 0.00167 -0.1031 0.5009 0.4485
0.250 0.5678 0.00730 0.00170 -0.1029 0.4922 0.4900
0.500 0.5958 0.00727 0.00173 -0.1028 0.4836 0.5179
0.750 0.6233 0.00731 0.00177 -0.1026 0.4748 0.5418
1.000 0.6508 0.00730 0.00182 -0.1024 0.4656 0.5729
1.250 0.6780 0.00733 0.00190 -0.1022 0.4565 0.6129
1.500 0.7052 0.00738 0.00200 -0.1020 0.4473 0.6503
1.750 0.7324 0.00744 0.00209 -0.1017 0.4390 0.6800
2.000 0.7595 0.00754 0.00217 -0.1015 0.4298 0.6956
2.250 0.7870 0.00762 0.00224 -0.1013 0.4217 0.7073
2.750 0.8413 0.00780 0.00240 -0.1009 0.4063 0.7330
3.000 0.8682 0.00789 0.00250 -0.1006 0.3991 0.7454
3.250 0.8950 0.00797 0.00259 -0.1003 0.3927 0.7611
3.500 0.9217 0.00801 0.00269 -0.1000 0.3864 0.7832
3.750 0.9468 0.00806 0.00281 -0.0994 0.3799 0.8181
4.000 0.9802 0.00786 0.00291 -0.1005 0.3738 1.0000
4.250 1.0072 0.00801 0.00302 -0.1003 0.3673 1.0000
4.500 1.0338 0.00818 0.00315 -0.1001 0.3613 1.0000
4.750 1.0610 0.00830 0.00326 -0.1000 0.3559 1.0000
5.000 1.0873 0.00849 0.00340 -0.0997 0.3488 1.0000
5.250 1.1140 0.00863 0.00353 -0.0995 0.3428 1.0000
5.500 1.1404 0.00880 0.00367 -0.0992 0.3360 1.0000
5.750 1.1662 0.00900 0.00383 -0.0989 0.3296 1.0000
6.000 1.1929 0.00913 0.00397 -0.0987 0.3244 1.0000
6.250 1.2187 0.00932 0.00414 -0.0984 0.3186 1.0000
6.500 1.2444 0.00951 0.00431 -0.0980 0.3126 1.0000
6.750 1.2702 0.00969 0.00448 -0.0977 0.3061 1.0000
7.000 1.2949 0.00993 0.00468 -0.0972 0.2988 1.0000
7.250 1.3206 0.01010 0.00486 -0.0969 0.2915 1.0000
7.500 1.3446 0.01037 0.00509 -0.0963 0.2828 1.0000
7.750 1.3694 0.01058 0.00529 -0.0959 0.2741 1.0000
8.000 1.3930 0.01086 0.00554 -0.0952 0.2640 1.0000
8.250 1.4153 0.01121 0.00582 -0.0944 0.2497 1.0000
8.500 1.4365 0.01162 0.00615 -0.0934 0.2329 1.0000
8.750 1.4549 0.01217 0.00658 -0.0920 0.2116 1.0000
9.000 1.4723 0.01274 0.00705 -0.0905 0.1941 1.0000
9.500 1.5087 0.01369 0.00791 -0.0876 0.1744 1.0000
9.750 1.5261 0.01415 0.00834 -0.0860 0.1683 1.0000
10.000 1.5438 0.01448 0.00870 -0.0844 0.1640 1.0000
10.250 1.5585 0.01491 0.00912 -0.0823 0.1587 1.0000
10.500 1.5712 0.01542 0.00962 -0.0799 0.1529 1.0000
10.750 1.5876 0.01579 0.01002 -0.0782 0.1474 1.0000
11.000 1.5981 0.01642 0.01062 -0.0757 0.1395 1.0000
11.250 1.6107 0.01699 0.01117 -0.0736 0.1293 1.0000
11.500 1.6039 0.01851 0.01245 -0.0691 0.0948 1.0000
11.750 1.5972 0.02016 0.01400 -0.0651 0.0775 1.0000
12.000 1.5991 0.02149 0.01533 -0.0624 0.0705 1.0000
12.250 1.6048 0.02271 0.01658 -0.0604 0.0670 1.0000
12.500 1.6084 0.02415 0.01805 -0.0584 0.0635 1.0000
12.750 1.6153 0.02547 0.01942 -0.0569 0.0611 1.0000
13.000 1.6217 0.02692 0.02092 -0.0556 0.0590 1.0000
13.250 1.6256 0.02865 0.02269 -0.0543 0.0569 1.0000
13.500 1.6286 0.03058 0.02466 -0.0532 0.0549 1.0000
13.750 1.6328 0.03249 0.02664 -0.0524 0.0532 1.0000
14.000 1.6394 0.03425 0.02847 -0.0517 0.0519 1.0000
14.250 1.6437 0.03630 0.03058 -0.0511 0.0505 1.0000
14.500 1.6452 0.03867 0.03300 -0.0506 0.0488 1.0000
14.750 1.6443 0.04134 0.03572 -0.0502 0.0470 1.0000
15.000 1.6458 0.04381 0.03826 -0.0499 0.0454 1.0000
15.250 1.6489 0.04616 0.04068 -0.0496 0.0440 1.0000
15.500 1.6484 0.04894 0.04352 -0.0495 0.0421 1.0000
15.750 1.6446 0.05218 0.04679 -0.0495 0.0401 1.0000
16.000 1.6443 0.05509 0.04976 -0.0496 0.0381 1.0000
16.250 1.6412 0.05840 0.05312 -0.0498 0.0355 1.0000
16.500 1.6355 0.06214 0.05691 -0.0502 0.0330 1.0000
16.750 1.6296 0.06602 0.06083 -0.0508 0.0298 1.0000
17.000 1.6224 0.07018 0.06505 -0.0515 0.0273 1.0000
17.250 1.6128 0.07478 0.06970 -0.0525 0.0247 1.0000
17.500 1.6044 0.07935 0.07433 -0.0536 0.0228 1.0000
17.750 1.5939 0.08430 0.07934 -0.0550 0.0212 1.0000
18.000 1.5846 0.08921 0.08433 -0.0564 0.0201 1.0000
18.250 1.5766 0.09401 0.08921 -0.0579 0.0193 1.0000
18.500 1.5665 0.09921 0.09449 -0.0597 0.0185 1.0000
18.750 1.5560 0.10455 0.09991 -0.0617 0.0178 1.0000
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