GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 375 AIRFOIL (goe375-il) Reynolds number: 1,000,000 Max Cl/Cd: 108.37 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe375-il-1000000-n5.txt Download as CSV file: xf-goe375-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 375 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3336 0.09745 0.09589 -0.0134 1.0000 0.0045
-8.250 -0.3299 0.09441 0.09287 -0.0143 1.0000 0.0045
-8.000 -0.3266 0.09162 0.09010 -0.0149 1.0000 0.0045
-7.750 -0.2124 0.06988 0.06844 -0.0286 0.9619 0.0049
-7.250 -0.3068 0.08215 0.08069 -0.0209 0.9808 0.0045
-7.000 -0.2729 0.07681 0.07532 -0.0306 0.9626 0.0044
-6.500 -0.1913 0.06573 0.06390 -0.0531 0.8737 0.0044
-6.250 -0.1785 0.06291 0.06093 -0.0553 0.8445 0.0048
-6.000 -0.1630 0.06095 0.05888 -0.0568 0.8272 0.0053
-5.750 -0.1460 0.05803 0.05587 -0.0592 0.8135 0.0059
-5.250 -0.1057 0.04861 0.04621 -0.0658 0.7906 0.0045
-5.000 -0.0835 0.04485 0.04233 -0.0681 0.7802 0.0045
-4.750 -0.0603 0.04126 0.03860 -0.0699 0.7675 0.0045
-4.500 -0.0369 0.03839 0.03558 -0.0711 0.7515 0.0047
-4.250 -0.0130 0.03588 0.03290 -0.0719 0.7329 0.0049
-4.000 0.0112 0.03375 0.03060 -0.0723 0.7104 0.0052
-3.750 0.0363 0.03095 0.02757 -0.0726 0.6876 0.0055
-3.500 0.0618 0.02790 0.02426 -0.0726 0.6637 0.0059
-3.250 0.0877 0.02377 0.01972 -0.0719 0.6385 0.0066
-3.000 0.1123 0.02192 0.01757 -0.0713 0.6039 0.0069
-2.750 0.1368 0.02077 0.01615 -0.0707 0.5665 0.0074
-2.500 0.1619 0.01891 0.01396 -0.0698 0.5357 0.0080
-2.250 0.1874 0.01630 0.01091 -0.0686 0.5120 0.0095
-2.000 0.2132 0.01609 0.01058 -0.0683 0.4911 0.0100
-1.750 0.2393 0.01510 0.00936 -0.0677 0.4742 0.0111
-1.500 0.2655 0.01339 0.00732 -0.0667 0.4596 0.0128
-1.250 0.2918 0.01337 0.00721 -0.0665 0.4435 0.0134
-0.750 0.3447 0.01180 0.00520 -0.0652 0.4118 0.0169
-0.500 0.3711 0.01174 0.00507 -0.0650 0.3974 0.0173
-0.250 0.3975 0.01153 0.00477 -0.0646 0.3830 0.0179
0.000 0.4238 0.01127 0.00439 -0.0642 0.3644 0.0186
0.250 0.4498 0.01107 0.00403 -0.0638 0.3405 0.0198
0.500 0.4759 0.01097 0.00374 -0.0633 0.3171 0.0210
0.750 0.5021 0.01103 0.00365 -0.0628 0.2958 0.0215
1.000 0.5278 0.01065 0.00319 -0.0624 0.2798 0.0220
1.250 0.5536 0.01041 0.00290 -0.0620 0.2668 0.0223
1.500 0.5795 0.01030 0.00275 -0.0616 0.2553 0.0229
1.750 0.6055 0.01017 0.00259 -0.0612 0.2460 0.0230
2.000 0.6314 0.01006 0.00244 -0.0608 0.2379 0.0231
2.250 0.6573 0.00999 0.00234 -0.0604 0.2300 0.0234
2.500 0.6834 0.00996 0.00229 -0.0600 0.2227 0.0240
2.750 0.7095 0.00997 0.00226 -0.0597 0.2156 0.0248
3.000 0.7357 0.00999 0.00227 -0.0593 0.2098 0.0257
3.250 0.7622 0.01001 0.00228 -0.0590 0.2052 0.0263
3.500 0.7884 0.01007 0.00231 -0.0587 0.2000 0.0267
3.750 0.8146 0.01014 0.00239 -0.0584 0.1953 0.0273
4.250 0.8672 0.01028 0.00252 -0.0579 0.1860 0.0277
4.500 0.8932 0.01036 0.00259 -0.0575 0.1810 0.0276
4.750 0.9194 0.01043 0.00267 -0.0572 0.1764 0.0276
5.000 0.9453 0.01055 0.00278 -0.0569 0.1706 0.0277
5.250 0.9712 0.01066 0.00289 -0.0566 0.1657 0.0280
5.500 0.9971 0.01079 0.00301 -0.0563 0.1601 0.0293
5.750 1.0226 0.01097 0.00316 -0.0559 0.1539 0.0319
6.000 1.0484 0.01111 0.00332 -0.0556 0.1493 0.0345
6.250 1.0738 0.01130 0.00352 -0.0552 0.1436 0.0393
6.750 1.1357 0.01048 0.00426 -0.0578 0.1226 1.0000
7.000 1.1598 0.01078 0.00452 -0.0572 0.1150 1.0000
7.250 1.1843 0.01104 0.00478 -0.0567 0.1091 1.0000
7.500 1.2078 0.01139 0.00509 -0.0561 0.0998 1.0000
7.750 1.2316 0.01172 0.00540 -0.0555 0.0901 1.0000
8.000 1.2419 0.01360 0.00677 -0.0531 0.0168 1.0000
8.250 1.2641 0.01408 0.00729 -0.0523 0.0105 1.0000
8.500 1.2866 0.01452 0.00776 -0.0516 0.0083 1.0000
8.750 1.3087 0.01499 0.00827 -0.0508 0.0068 1.0000
9.000 1.3309 0.01543 0.00876 -0.0500 0.0060 1.0000
9.250 1.3520 0.01597 0.00933 -0.0491 0.0050 1.0000
9.500 1.3732 0.01648 0.00992 -0.0482 0.0044 1.0000
9.750 1.3943 0.01698 0.01047 -0.0473 0.0040 1.0000
10.000 1.4145 0.01754 0.01107 -0.0463 0.0035 1.0000
10.250 1.4336 0.01819 0.01179 -0.0452 0.0032 1.0000
10.500 1.4517 0.01890 0.01259 -0.0439 0.0029 1.0000
10.750 1.4696 0.01958 0.01335 -0.0427 0.0028 1.0000
11.000 1.4871 0.02026 0.01411 -0.0414 0.0026 1.0000
11.250 1.5028 0.02102 0.01496 -0.0399 0.0024 1.0000
11.500 1.5176 0.02181 0.01583 -0.0382 0.0023 1.0000
11.750 1.5313 0.02260 0.01669 -0.0365 0.0021 1.0000
12.000 1.5404 0.02347 0.01765 -0.0340 0.0020 1.0000
12.250 1.5458 0.02448 0.01875 -0.0310 0.0019 1.0000
12.500 1.5464 0.02582 0.02022 -0.0278 0.0018 1.0000
12.750 1.5463 0.02730 0.02182 -0.0249 0.0018 1.0000
13.000 1.5532 0.02841 0.02302 -0.0231 0.0017 1.0000
13.250 1.5550 0.02999 0.02472 -0.0212 0.0016 1.0000
13.500 1.5539 0.03200 0.02685 -0.0196 0.0015 1.0000
13.750 1.5495 0.03453 0.02952 -0.0184 0.0015 1.0000
14.000 1.5454 0.03730 0.03241 -0.0178 0.0015 1.0000
14.250 1.5392 0.04058 0.03582 -0.0178 0.0015 1.0000
14.500 1.5306 0.04452 0.03991 -0.0185 0.0014 1.0000
14.750 1.5199 0.04917 0.04470 -0.0200 0.0014 1.0000
15.000 1.5024 0.05543 0.05113 -0.0227 0.0014 1.0000
15.250 1.4877 0.06155 0.05740 -0.0255 0.0014 1.0000
15.500 1.4598 0.07013 0.06615 -0.0295 0.0015 1.0000
15.750 1.4380 0.07763 0.07379 -0.0328 0.0015 1.0000
16.000 1.4094 0.08648 0.08279 -0.0368 0.0015 1.0000
16.250 1.3800 0.09566 0.09211 -0.0409 0.0015 1.0000
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Polar data table (+)
Polar graphs
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