GOE 412 AIRFOIL (goe412-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 412 AIRFOIL (goe412-il) Reynolds number: 500,000 Max Cl/Cd: 103.24 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe412-il-500000-n5.txt Download as CSV file: xf-goe412-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 412 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.5305 0.03522 0.03189 -0.1217 0.9192 0.0231
-10.750 -0.5270 0.03198 0.02834 -0.1224 0.9073 0.0234
-10.500 -0.5166 0.02968 0.02576 -0.1222 0.8952 0.0237
-10.250 -0.5026 0.02778 0.02358 -0.1219 0.8829 0.0241
-9.750 -0.4683 0.02464 0.01986 -0.1210 0.8584 0.0247
-9.500 -0.4484 0.02340 0.01835 -0.1205 0.8475 0.0250
-9.250 -0.4269 0.02238 0.01707 -0.1201 0.8379 0.0252
-9.000 -0.4043 0.02149 0.01596 -0.1198 0.8289 0.0254
-8.750 -0.3816 0.02051 0.01477 -0.1194 0.8211 0.0256
-8.500 -0.3599 0.01919 0.01329 -0.1191 0.8136 0.0260
-8.000 -0.3109 0.01773 0.01159 -0.1187 0.8010 0.0267
-7.750 -0.2858 0.01710 0.01084 -0.1185 0.7948 0.0269
-7.500 -0.2603 0.01652 0.01014 -0.1183 0.7894 0.0272
-7.250 -0.2343 0.01595 0.00949 -0.1182 0.7839 0.0275
-7.000 -0.2082 0.01544 0.00887 -0.1180 0.7784 0.0277
-6.500 -0.1552 0.01450 0.00775 -0.1178 0.7685 0.0283
-6.250 -0.1285 0.01408 0.00724 -0.1177 0.7634 0.0287
-6.000 -0.1017 0.01369 0.00676 -0.1176 0.7585 0.0290
-5.750 -0.0746 0.01334 0.00634 -0.1175 0.7540 0.0294
-5.500 -0.0473 0.01302 0.00596 -0.1175 0.7491 0.0298
-5.250 -0.0200 0.01273 0.00561 -0.1174 0.7443 0.0302
-4.750 0.0349 0.01218 0.00494 -0.1174 0.7353 0.0307
-4.500 0.0620 0.01180 0.00453 -0.1173 0.7305 0.0311
-4.250 0.0893 0.01151 0.00419 -0.1172 0.7259 0.0317
-4.000 0.1170 0.01127 0.00392 -0.1172 0.7216 0.0322
-3.750 0.1449 0.01106 0.00368 -0.1173 0.7170 0.0328
-3.500 0.1727 0.01088 0.00347 -0.1173 0.7121 0.0335
-3.250 0.2006 0.01074 0.00327 -0.1173 0.7078 0.0342
-3.000 0.2287 0.01059 0.00310 -0.1173 0.7034 0.0350
-2.750 0.2568 0.01047 0.00295 -0.1174 0.6985 0.0359
-2.500 0.2848 0.01036 0.00281 -0.1174 0.6938 0.0374
-2.250 0.3127 0.01023 0.00267 -0.1174 0.6895 0.0402
-2.000 0.3408 0.01009 0.00256 -0.1175 0.6846 0.0455
-1.750 0.3684 0.00994 0.00249 -0.1175 0.6790 0.0693
-1.500 0.3962 0.00988 0.00242 -0.1175 0.6732 0.0813
-1.250 0.4240 0.00979 0.00237 -0.1175 0.6665 0.0906
-1.000 0.4516 0.00974 0.00233 -0.1175 0.6601 0.1017
-0.750 0.4793 0.00968 0.00231 -0.1175 0.6530 0.1197
-0.500 0.5064 0.00965 0.00228 -0.1174 0.6434 0.1374
-0.250 0.5337 0.00961 0.00225 -0.1173 0.6333 0.1525
0.000 0.5608 0.00958 0.00223 -0.1172 0.6257 0.1685
0.250 0.5882 0.00946 0.00225 -0.1172 0.6191 0.2086
0.500 0.6151 0.00936 0.00230 -0.1171 0.6121 0.2727
0.750 0.6424 0.00932 0.00233 -0.1171 0.6054 0.3072
1.000 0.6692 0.00926 0.00236 -0.1170 0.5973 0.3490
1.250 0.6947 0.00898 0.00244 -0.1168 0.5892 0.4777
1.500 0.7191 0.00869 0.00252 -0.1163 0.5804 0.6221
1.750 0.7457 0.00806 0.00272 -0.1156 0.5729 0.9429
2.000 0.7921 0.00818 0.00278 -0.1198 0.5635 0.9975
2.250 0.8195 0.00830 0.00285 -0.1198 0.5532 1.0000
2.500 0.8438 0.00844 0.00292 -0.1191 0.5424 1.0000
2.750 0.8684 0.00858 0.00301 -0.1185 0.5321 1.0000
3.000 0.8933 0.00872 0.00310 -0.1180 0.5225 1.0000
3.250 0.9172 0.00890 0.00321 -0.1173 0.5102 1.0000
3.500 0.9405 0.00911 0.00334 -0.1164 0.4943 1.0000
3.750 0.9633 0.00935 0.00349 -0.1155 0.4767 1.0000
4.000 0.9860 0.00960 0.00365 -0.1146 0.4595 1.0000
4.250 1.0082 0.00987 0.00384 -0.1136 0.4416 1.0000
4.500 1.0300 0.01017 0.00405 -0.1126 0.4236 1.0000
5.000 1.0704 0.01091 0.00456 -0.1100 0.3799 1.0000
5.250 1.0898 0.01131 0.00486 -0.1086 0.3587 1.0000
5.500 1.1099 0.01168 0.00514 -0.1073 0.3424 1.0000
5.750 1.1300 0.01203 0.00543 -0.1060 0.3282 1.0000
6.000 1.1497 0.01238 0.00574 -0.1047 0.3148 1.0000
6.250 1.1677 0.01275 0.00605 -0.1030 0.3021 1.0000
6.500 1.1850 0.01315 0.00640 -0.1013 0.2889 1.0000
6.750 1.2023 0.01356 0.00676 -0.0996 0.2750 1.0000
7.000 1.2190 0.01403 0.00718 -0.0978 0.2598 1.0000
7.250 1.2351 0.01455 0.00763 -0.0960 0.2433 1.0000
7.500 1.2494 0.01516 0.00816 -0.0940 0.2229 1.0000
8.250 1.2899 0.01728 0.01005 -0.0881 0.1778 1.0000
8.500 1.3045 0.01796 0.01070 -0.0863 0.1701 1.0000
8.750 1.3211 0.01855 0.01130 -0.0850 0.1648 1.0000
9.000 1.3364 0.01922 0.01198 -0.0835 0.1596 1.0000
9.250 1.3513 0.01993 0.01269 -0.0820 0.1549 1.0000
9.500 1.3688 0.02050 0.01332 -0.0808 0.1514 1.0000
9.750 1.3841 0.02122 0.01405 -0.0795 0.1456 1.0000
10.000 1.3974 0.02208 0.01491 -0.0780 0.1394 1.0000
10.250 1.4131 0.02281 0.01568 -0.0768 0.1320 1.0000
10.500 1.4257 0.02377 0.01662 -0.0754 0.1195 1.0000
10.750 1.4250 0.02570 0.01830 -0.0727 0.0863 1.0000
11.000 1.4323 0.02711 0.01970 -0.0709 0.0779 1.0000
11.250 1.4394 0.02859 0.02118 -0.0692 0.0714 1.0000
11.500 1.4506 0.02978 0.02243 -0.0679 0.0667 1.0000
11.750 1.4580 0.03128 0.02394 -0.0664 0.0599 1.0000
12.000 1.4632 0.03299 0.02562 -0.0648 0.0478 1.0000
12.250 1.4557 0.03583 0.02829 -0.0624 0.0253 1.0000
12.500 1.4577 0.03794 0.03040 -0.0608 0.0200 1.0000
12.750 1.4627 0.03986 0.03236 -0.0595 0.0178 1.0000
13.000 1.4684 0.04174 0.03431 -0.0584 0.0164 1.0000
13.250 1.4746 0.04362 0.03626 -0.0574 0.0154 1.0000
13.500 1.4795 0.04566 0.03837 -0.0564 0.0146 1.0000
13.750 1.4829 0.04789 0.04067 -0.0555 0.0139 1.0000
14.000 1.4866 0.05015 0.04300 -0.0546 0.0133 1.0000
14.250 1.4915 0.05232 0.04526 -0.0539 0.0129 1.0000
14.500 1.4951 0.05467 0.04770 -0.0533 0.0124 1.0000
14.750 1.4977 0.05717 0.05029 -0.0527 0.0120 1.0000
15.000 1.4994 0.05983 0.05303 -0.0521 0.0117 1.0000
15.250 1.4999 0.06268 0.05597 -0.0517 0.0114 1.0000
15.500 1.4991 0.06576 0.05913 -0.0514 0.0111 1.0000
15.750 1.4963 0.06913 0.06259 -0.0511 0.0108 1.0000
16.000 1.4912 0.07285 0.06642 -0.0510 0.0106 1.0000
16.250 1.4898 0.07619 0.06985 -0.0510 0.0104 1.0000
16.500 1.4879 0.07964 0.07342 -0.0511 0.0102 1.0000
16.750 1.4851 0.08327 0.07715 -0.0514 0.0100 1.0000
17.000 1.4815 0.08702 0.08101 -0.0517 0.0098 1.0000
17.250 1.4770 0.09096 0.08505 -0.0522 0.0096 1.0000
17.500 1.4718 0.09507 0.08926 -0.0528 0.0095 1.0000
17.750 1.4661 0.09933 0.09363 -0.0536 0.0093 1.0000
18.000 1.4598 0.10371 0.09811 -0.0545 0.0091 1.0000
18.250 1.4530 0.10821 0.10271 -0.0556 0.0090 1.0000
18.500 1.4459 0.11282 0.10742 -0.0568 0.0088 1.0000
18.750 1.4384 0.11756 0.11226 -0.0582 0.0087 1.0000
19.000 1.4305 0.12243 0.11723 -0.0598 0.0086 1.0000
19.250 1.4223 0.12741 0.12231 -0.0616 0.0085 1.0000
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