GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 532 AIRFOIL (goe532-il) Reynolds number: 500,000 Max Cl/Cd: 89.74 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe532-il-500000-n5.txt Download as CSV file: xf-goe532-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 532 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3213 0.09567 0.09320 -0.0389 1.0000 0.0206
-10.250 -0.3168 0.09335 0.09091 -0.0392 1.0000 0.0209
-9.750 -0.4560 0.03335 0.03000 -0.1041 0.9384 0.0239
-9.500 -0.4247 0.03154 0.02804 -0.1077 0.9219 0.0241
-9.250 -0.3990 0.02980 0.02609 -0.1099 0.9019 0.0243
-9.000 -0.3788 0.02806 0.02411 -0.1107 0.8822 0.0246
-8.750 -0.3602 0.02635 0.02215 -0.1108 0.8650 0.0248
-8.500 -0.3416 0.02464 0.02017 -0.1106 0.8491 0.0251
-8.250 -0.3223 0.02301 0.01824 -0.1102 0.8339 0.0254
-8.000 -0.3021 0.02147 0.01640 -0.1097 0.8186 0.0258
-7.750 -0.2805 0.02013 0.01477 -0.1092 0.8034 0.0263
-7.500 -0.2578 0.01900 0.01335 -0.1086 0.7879 0.0268
-7.250 -0.2344 0.01802 0.01210 -0.1080 0.7720 0.0271
-7.000 -0.2102 0.01724 0.01107 -0.1074 0.7545 0.0274
-6.750 -0.1862 0.01643 0.01007 -0.1067 0.7344 0.0276
-6.500 -0.1620 0.01579 0.00927 -0.1061 0.7114 0.0278
-6.250 -0.1374 0.01533 0.00866 -0.1054 0.6860 0.0281
-6.000 -0.1126 0.01494 0.00812 -0.1047 0.6621 0.0284
-5.750 -0.0873 0.01458 0.00762 -0.1041 0.6423 0.0287
-5.500 -0.0616 0.01423 0.00714 -0.1036 0.6257 0.0290
-5.250 -0.0355 0.01389 0.00670 -0.1031 0.6121 0.0294
-5.000 -0.0093 0.01360 0.00629 -0.1026 0.6000 0.0299
-4.750 0.0172 0.01329 0.00589 -0.1022 0.5883 0.0304
-4.500 0.0437 0.01299 0.00549 -0.1018 0.5760 0.0308
-4.250 0.0700 0.01273 0.00512 -0.1013 0.5630 0.0311
-4.000 0.0965 0.01250 0.00479 -0.1008 0.5492 0.0314
-3.750 0.1233 0.01226 0.00448 -0.1004 0.5377 0.0317
-3.500 0.1496 0.01196 0.00412 -0.1000 0.5272 0.0322
-3.250 0.1766 0.01174 0.00388 -0.0996 0.5180 0.0327
-3.000 0.2036 0.01158 0.00367 -0.0993 0.5104 0.0333
-2.750 0.2310 0.01141 0.00347 -0.0990 0.5031 0.0338
-2.500 0.2582 0.01129 0.00330 -0.0986 0.4958 0.0346
-2.250 0.2857 0.01118 0.00315 -0.0983 0.4894 0.0355
-2.000 0.3131 0.01109 0.00301 -0.0980 0.4815 0.0363
-1.750 0.3402 0.01096 0.00285 -0.0977 0.4746 0.0373
-1.500 0.3678 0.01086 0.00273 -0.0974 0.4685 0.0383
-1.250 0.3953 0.01080 0.00264 -0.0971 0.4621 0.0396
-1.000 0.4227 0.01076 0.00256 -0.0968 0.4561 0.0411
-0.750 0.4503 0.01070 0.00249 -0.0966 0.4499 0.0432
-0.500 0.4777 0.01067 0.00244 -0.0963 0.4440 0.0468
-0.250 0.5051 0.01064 0.00241 -0.0960 0.4392 0.0536
0.000 0.5327 0.01055 0.00238 -0.0957 0.4336 0.0724
0.250 0.5589 0.01016 0.00236 -0.0955 0.4278 0.2070
0.500 0.5854 0.00997 0.00241 -0.0952 0.4232 0.3004
0.750 0.6125 0.00982 0.00247 -0.0950 0.4187 0.3754
1.000 0.6393 0.00972 0.00254 -0.0947 0.4135 0.4429
1.250 0.6653 0.00962 0.00264 -0.0942 0.4079 0.5262
1.500 0.6907 0.00947 0.00277 -0.0936 0.4013 0.6236
1.750 0.7158 0.00938 0.00287 -0.0929 0.3939 0.7009
2.000 0.7403 0.00931 0.00295 -0.0919 0.3869 0.7656
2.250 0.7766 0.00902 0.00301 -0.0934 0.3765 0.9375
2.500 0.8079 0.00917 0.00308 -0.0940 0.3647 1.0000
2.750 0.8341 0.00935 0.00317 -0.0936 0.3507 1.0000
3.000 0.8597 0.00958 0.00328 -0.0931 0.3304 1.0000
3.250 0.8832 0.00998 0.00345 -0.0923 0.2926 1.0000
3.500 0.9038 0.01066 0.00380 -0.0911 0.2383 1.0000
3.750 0.9264 0.01116 0.00413 -0.0902 0.2108 1.0000
4.000 0.9505 0.01151 0.00438 -0.0895 0.1976 1.0000
4.250 0.9751 0.01182 0.00461 -0.0889 0.1895 1.0000
4.500 1.0001 0.01208 0.00484 -0.0883 0.1842 1.0000
4.750 1.0253 0.01231 0.00504 -0.0878 0.1807 1.0000
5.000 1.0501 0.01256 0.00527 -0.0872 0.1774 1.0000
5.250 1.0746 0.01283 0.00551 -0.0866 0.1743 1.0000
5.500 1.0989 0.01311 0.00577 -0.0859 0.1711 1.0000
5.750 1.1235 0.01334 0.00600 -0.0853 0.1687 1.0000
6.000 1.1481 0.01358 0.00625 -0.0847 0.1666 1.0000
6.250 1.1722 0.01383 0.00650 -0.0841 0.1644 1.0000
6.500 1.1960 0.01409 0.00676 -0.0834 0.1622 1.0000
6.750 1.2193 0.01438 0.00706 -0.0826 0.1596 1.0000
7.000 1.2418 0.01471 0.00737 -0.0817 0.1568 1.0000
7.250 1.2641 0.01503 0.00770 -0.0808 0.1539 1.0000
7.500 1.2875 0.01526 0.00797 -0.0801 0.1520 1.0000
7.750 1.3103 0.01553 0.00825 -0.0793 0.1486 1.0000
8.000 1.3321 0.01584 0.00857 -0.0783 0.1450 1.0000
8.250 1.3523 0.01622 0.00893 -0.0771 0.1407 1.0000
8.500 1.3735 0.01652 0.00926 -0.0761 0.1363 1.0000
8.750 1.3925 0.01691 0.00962 -0.0748 0.1257 1.0000
9.250 1.4096 0.01850 0.01093 -0.0689 0.0860 1.0000
9.500 1.4220 0.01912 0.01156 -0.0667 0.0832 1.0000
9.750 1.4340 0.01977 0.01224 -0.0645 0.0811 1.0000
10.000 1.4453 0.02049 0.01298 -0.0623 0.0792 1.0000
10.250 1.4571 0.02120 0.01374 -0.0603 0.0778 1.0000
10.500 1.4698 0.02189 0.01449 -0.0585 0.0768 1.0000
10.750 1.4814 0.02268 0.01534 -0.0568 0.0757 1.0000
11.000 1.4916 0.02360 0.01631 -0.0550 0.0745 1.0000
11.250 1.5003 0.02465 0.01743 -0.0532 0.0733 1.0000
11.500 1.5082 0.02583 0.01866 -0.0516 0.0723 1.0000
11.750 1.5145 0.02719 0.02008 -0.0499 0.0713 1.0000
12.000 1.5199 0.02871 0.02166 -0.0485 0.0704 1.0000
12.250 1.5231 0.03049 0.02351 -0.0471 0.0695 1.0000
12.500 1.5296 0.03210 0.02520 -0.0461 0.0689 1.0000
12.750 1.5368 0.03372 0.02689 -0.0452 0.0684 1.0000
13.000 1.5431 0.03548 0.02875 -0.0445 0.0678 1.0000
13.250 1.5482 0.03745 0.03079 -0.0439 0.0671 1.0000
13.500 1.5523 0.03957 0.03300 -0.0434 0.0665 1.0000
13.750 1.5560 0.04181 0.03534 -0.0431 0.0659 1.0000
14.000 1.5591 0.04418 0.03778 -0.0428 0.0652 1.0000
14.250 1.5606 0.04678 0.04046 -0.0427 0.0645 1.0000
14.500 1.5617 0.04947 0.04324 -0.0427 0.0639 1.0000
14.750 1.5618 0.05235 0.04619 -0.0427 0.0632 1.0000
15.000 1.5609 0.05539 0.04932 -0.0429 0.0626 1.0000
15.250 1.5585 0.05868 0.05267 -0.0432 0.0619 1.0000
15.500 1.5543 0.06223 0.05630 -0.0437 0.0612 1.0000
15.750 1.5565 0.06509 0.05924 -0.0441 0.0604 1.0000
16.000 1.5593 0.06789 0.06214 -0.0446 0.0596 1.0000
16.250 1.5617 0.07077 0.06511 -0.0451 0.0587 1.0000
16.500 1.5626 0.07390 0.06833 -0.0457 0.0579 1.0000
16.750 1.5629 0.07716 0.07168 -0.0465 0.0572 1.0000
17.000 1.5629 0.08048 0.07507 -0.0473 0.0564 1.0000
17.250 1.5616 0.08407 0.07873 -0.0483 0.0555 1.0000
17.500 1.5591 0.08787 0.08260 -0.0494 0.0546 1.0000
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