GOE 572 AIRFOIL (goe572-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 572 AIRFOIL (goe572-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.64 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe572-il-1000000-n5.txt Download as CSV file: xf-goe572-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 572 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
------ -------- --------- --------- -------- -------- --------
-13.500 -0.3926 0.02960 0.02542 -0.1670 0.5938 0.0086
-13.250 -0.4167 0.02694 0.02253 -0.1614 0.5874 0.0086
-13.000 -0.4286 0.02541 0.02085 -0.1560 0.5817 0.0088
-12.750 -0.4279 0.02428 0.01956 -0.1523 0.5729 0.0087
-12.500 -0.4291 0.02289 0.01802 -0.1482 0.5666 0.0089
-12.250 -0.4246 0.02179 0.01678 -0.1448 0.5603 0.0092
-12.000 -0.4148 0.02102 0.01589 -0.1420 0.5542 0.0094
-11.750 -0.4047 0.02018 0.01494 -0.1391 0.5476 0.0096
-11.500 -0.3922 0.01953 0.01416 -0.1366 0.5414 0.0097
-11.250 -0.3786 0.01889 0.01341 -0.1341 0.5361 0.0100
-11.000 -0.3635 0.01832 0.01274 -0.1319 0.5309 0.0102
-10.750 -0.3480 0.01779 0.01209 -0.1296 0.5254 0.0104
-10.500 -0.3312 0.01733 0.01153 -0.1275 0.5208 0.0108
-10.250 -0.3139 0.01686 0.01095 -0.1255 0.5155 0.0110
-10.000 -0.2964 0.01641 0.01041 -0.1235 0.5106 0.0112
-9.500 -0.2600 0.01557 0.00941 -0.1197 0.5019 0.0120
-9.250 -0.2403 0.01523 0.00900 -0.1181 0.4973 0.0125
-9.000 -0.2206 0.01492 0.00861 -0.1164 0.4928 0.0130
-8.750 -0.2006 0.01465 0.00826 -0.1147 0.4882 0.0135
-8.500 -0.1798 0.01435 0.00789 -0.1132 0.4841 0.0140
-8.250 -0.1591 0.01407 0.00755 -0.1117 0.4803 0.0146
-8.000 -0.1376 0.01388 0.00732 -0.1103 0.4760 0.0153
-7.750 -0.1165 0.01370 0.00708 -0.1088 0.4718 0.0159
-7.500 -0.0946 0.01348 0.00681 -0.1075 0.4679 0.0166
-7.250 -0.0729 0.01329 0.00654 -0.1061 0.4641 0.0172
-7.000 -0.0515 0.01310 0.00631 -0.1046 0.4601 0.0178
-6.750 -0.0296 0.01299 0.00616 -0.1033 0.4564 0.0185
-6.500 -0.0069 0.01287 0.00602 -0.1021 0.4534 0.0193
-6.250 0.0155 0.01273 0.00584 -0.1009 0.4499 0.0200
-6.000 0.0375 0.01260 0.00564 -0.0995 0.4461 0.0206
-5.750 0.0589 0.01250 0.00547 -0.0981 0.4414 0.0212
-5.500 0.0808 0.01239 0.00534 -0.0967 0.4378 0.0220
-5.250 0.1028 0.01229 0.00523 -0.0954 0.4346 0.0227
-5.000 0.1238 0.01218 0.00509 -0.0939 0.4313 0.0233
-4.750 0.1442 0.01210 0.00496 -0.0922 0.4275 0.0240
-4.500 0.1643 0.01206 0.00485 -0.0905 0.4233 0.0248
-4.250 0.1853 0.01194 0.00470 -0.0889 0.4195 0.0252
-4.000 0.2061 0.01184 0.00456 -0.0873 0.4160 0.0256
-3.750 0.2256 0.01167 0.00435 -0.0855 0.4126 0.0264
-3.500 0.2463 0.01162 0.00428 -0.0840 0.4090 0.0274
-3.250 0.2675 0.01156 0.00419 -0.0825 0.4060 0.0281
-3.000 0.2890 0.01148 0.00409 -0.0811 0.4024 0.0289
-2.750 0.3102 0.01142 0.00399 -0.0797 0.3990 0.0295
-2.500 0.3305 0.01139 0.00391 -0.0781 0.3945 0.0300
-2.250 0.3507 0.01135 0.00382 -0.0765 0.3908 0.0304
-2.000 0.3720 0.01129 0.00374 -0.0751 0.3879 0.0312
-1.750 0.3929 0.01123 0.00365 -0.0736 0.3845 0.0320
-1.500 0.4133 0.01123 0.00362 -0.0721 0.3799 0.0328
-1.250 0.4337 0.01125 0.00361 -0.0705 0.3755 0.0336
-1.000 0.4556 0.01123 0.00358 -0.0693 0.3733 0.0345
-0.750 0.4770 0.01125 0.00357 -0.0680 0.3695 0.0356
-0.500 0.4975 0.01129 0.00357 -0.0665 0.3654 0.0362
0.000 0.5386 0.01137 0.00361 -0.0636 0.3568 0.0394
0.250 0.5598 0.01141 0.00364 -0.0624 0.3534 0.0411
0.500 0.5801 0.01149 0.00368 -0.0609 0.3491 0.0429
0.750 0.6007 0.01155 0.00374 -0.0596 0.3464 0.0477
1.000 0.6218 0.01160 0.00379 -0.0583 0.3437 0.0529
1.250 0.6430 0.01164 0.00386 -0.0571 0.3406 0.0614
1.500 0.6639 0.01170 0.00394 -0.0559 0.3374 0.0729
1.750 0.6847 0.01177 0.00403 -0.0547 0.3345 0.0892
2.000 0.7044 0.01187 0.00416 -0.0534 0.3309 0.1118
2.250 0.7266 0.01187 0.00427 -0.0525 0.3288 0.1589
2.500 0.7492 0.01185 0.00441 -0.0518 0.3264 0.2228
2.750 0.7758 0.01167 0.00461 -0.0522 0.3227 0.3880
3.250 1.1561 0.01172 0.00582 -0.1248 0.3080 1.0000
3.500 1.1719 0.01189 0.00596 -0.1226 0.3054 1.0000
3.750 1.1877 0.01207 0.00612 -0.1205 0.3030 1.0000
4.000 1.2042 0.01226 0.00629 -0.1186 0.3006 1.0000
4.250 1.2221 0.01242 0.00645 -0.1169 0.2990 1.0000
4.500 1.2395 0.01259 0.00662 -0.1152 0.2971 1.0000
4.750 1.2569 0.01278 0.00680 -0.1135 0.2951 1.0000
5.000 1.2738 0.01300 0.00701 -0.1117 0.2927 1.0000
5.250 1.2897 0.01325 0.00724 -0.1098 0.2903 1.0000
5.500 1.3055 0.01352 0.00750 -0.1080 0.2879 1.0000
5.750 1.3213 0.01379 0.00777 -0.1062 0.2856 1.0000
6.000 1.3386 0.01403 0.00802 -0.1046 0.2843 1.0000
6.250 1.3559 0.01428 0.00828 -0.1031 0.2827 1.0000
6.500 1.3724 0.01457 0.00858 -0.1015 0.2810 1.0000
6.750 1.3884 0.01489 0.00890 -0.0999 0.2788 1.0000
7.000 1.4035 0.01526 0.00927 -0.0982 0.2765 1.0000
7.250 1.4156 0.01576 0.00976 -0.0961 0.2724 1.0000
7.500 1.4306 0.01617 0.01018 -0.0945 0.2704 1.0000
7.750 1.4458 0.01659 0.01062 -0.0931 0.2675 1.0000
8.000 1.4604 0.01707 0.01111 -0.0915 0.2650 1.0000
8.250 1.4681 0.01788 0.01188 -0.0892 0.2580 1.0000
8.500 1.4808 0.01850 0.01251 -0.0876 0.2555 1.0000
8.750 1.4940 0.01912 0.01316 -0.0861 0.2524 1.0000
9.000 1.5018 0.02006 0.01407 -0.0841 0.2460 1.0000
9.250 1.5089 0.02110 0.01511 -0.0821 0.2412 1.0000
9.500 1.5182 0.02205 0.01607 -0.0805 0.2361 1.0000
9.750 1.5192 0.02358 0.01757 -0.0782 0.2283 1.0000
10.000 1.5260 0.02482 0.01884 -0.0767 0.2239 1.0000
10.250 1.5316 0.02621 0.02023 -0.0751 0.2193 1.0000
10.500 1.5294 0.02822 0.02224 -0.0731 0.2127 1.0000
10.750 1.5278 0.03030 0.02433 -0.0714 0.2051 1.0000
11.000 1.5221 0.03282 0.02684 -0.0695 0.1983 1.0000
11.250 1.5121 0.03580 0.02982 -0.0677 0.1892 1.0000
11.750 1.4664 0.04460 0.03860 -0.0634 0.1627 1.0000
12.000 1.4297 0.05066 0.04465 -0.0613 0.1422 1.0000
12.250 1.4064 0.05562 0.04964 -0.0599 0.1295 1.0000
12.500 1.3729 0.06183 0.05590 -0.0584 0.1127 1.0000
12.750 1.3472 0.06743 0.06155 -0.0575 0.1004 1.0000
13.000 1.3336 0.07173 0.06590 -0.0569 0.0932 1.0000
13.250 1.3027 0.07824 0.07243 -0.0562 0.0756 1.0000
13.500 1.2688 0.08531 0.07948 -0.0557 0.0535 1.0000
13.750 1.2429 0.09160 0.08580 -0.0555 0.0367 1.0000
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