GOE 511 AIRFOIL (goe511-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 511 AIRFOIL (goe511-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.87 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe511-il-1000000-n5.txt Download as CSV file: xf-goe511-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 511 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
------ -------- --------- --------- -------- -------- --------
-14.000 0.0898 0.10677 0.10460 -0.1364 0.9419 0.0159
-13.500 -0.3391 0.03210 0.02906 -0.1874 0.9198 0.0222
-13.250 -0.3490 0.02757 0.02429 -0.1871 0.9139 0.0223
-13.000 -0.3368 0.02505 0.02159 -0.1875 0.9102 0.0225
-12.750 -0.3210 0.02444 0.02094 -0.1860 0.9062 0.0226
-12.500 -0.3281 0.02306 0.01942 -0.1810 0.9003 0.0226
-12.250 -0.3117 0.02250 0.01879 -0.1794 0.8955 0.0228
-12.000 -0.2931 0.02179 0.01800 -0.1784 0.8912 0.0229
-11.750 -0.2845 0.02118 0.01732 -0.1751 0.8865 0.0230
-11.500 -0.2751 0.02046 0.01651 -0.1721 0.8801 0.0231
-11.250 -0.2588 0.01975 0.01568 -0.1703 0.8738 0.0233
-11.000 -0.2491 0.01914 0.01498 -0.1671 0.8675 0.0234
-10.750 -0.2352 0.01856 0.01431 -0.1646 0.8597 0.0235
-10.500 -0.2219 0.01792 0.01356 -0.1620 0.8517 0.0237
-10.250 -0.2079 0.01740 0.01291 -0.1594 0.8391 0.0238
-10.000 -0.1955 0.01697 0.01234 -0.1563 0.8164 0.0240
-9.750 -0.1947 0.01676 0.01184 -0.1507 0.7671 0.0241
-9.500 -0.1961 0.01663 0.01146 -0.1446 0.7288 0.0242
-9.250 -0.1912 0.01636 0.01101 -0.1399 0.7054 0.0243
-9.000 -0.1858 0.01614 0.01063 -0.1352 0.6823 0.0245
-8.750 -0.1809 0.01596 0.01031 -0.1304 0.6614 0.0247
-8.500 -0.1759 0.01573 0.00993 -0.1256 0.6393 0.0248
-8.250 -0.1696 0.01552 0.00955 -0.1210 0.6134 0.0249
-8.000 -0.1613 0.01532 0.00920 -0.1169 0.5882 0.0250
-7.750 -0.1514 0.01510 0.00883 -0.1131 0.5679 0.0252
-7.500 -0.1385 0.01485 0.00846 -0.1099 0.5533 0.0252
-7.250 -0.1238 0.01463 0.00813 -0.1071 0.5413 0.0253
-7.000 -0.1061 0.01443 0.00783 -0.1048 0.5318 0.0255
-6.750 -0.0906 0.01415 0.00746 -0.1022 0.5219 0.0256
-6.500 -0.0733 0.01380 0.00704 -0.0999 0.5154 0.0258
-6.250 -0.0560 0.01356 0.00673 -0.0976 0.5077 0.0259
-6.000 -0.0371 0.01338 0.00651 -0.0956 0.5019 0.0262
-5.750 -0.0166 0.01316 0.00624 -0.0939 0.4976 0.0263
-5.500 0.0042 0.01301 0.00605 -0.0922 0.4925 0.0265
-5.250 0.0244 0.01288 0.00587 -0.0905 0.4872 0.0267
-5.000 0.0447 0.01278 0.00572 -0.0887 0.4821 0.0269
-4.750 0.0662 0.01265 0.00556 -0.0872 0.4776 0.0272
-4.500 0.0871 0.01254 0.00541 -0.0856 0.4717 0.0274
-4.250 0.1077 0.01246 0.00528 -0.0840 0.4663 0.0277
-4.000 0.1289 0.01236 0.00513 -0.0824 0.4618 0.0279
-3.750 0.1513 0.01227 0.00501 -0.0811 0.4578 0.0283
-3.500 0.1733 0.01219 0.00489 -0.0797 0.4531 0.0285
-3.250 0.1946 0.01215 0.00481 -0.0782 0.4477 0.0288
-3.000 0.2156 0.01210 0.00471 -0.0767 0.4432 0.0290
-2.750 0.2377 0.01203 0.00462 -0.0753 0.4386 0.0292
-2.500 0.2589 0.01194 0.00450 -0.0739 0.4333 0.0296
-2.250 0.2792 0.01190 0.00441 -0.0722 0.4267 0.0300
-2.000 0.3012 0.01184 0.00434 -0.0709 0.4216 0.0303
-1.750 0.3230 0.01182 0.00429 -0.0695 0.4154 0.0308
-1.500 0.3443 0.01183 0.00426 -0.0681 0.4100 0.0311
-1.250 0.3656 0.01182 0.00423 -0.0667 0.4045 0.0315
-1.000 0.3870 0.01183 0.00421 -0.0653 0.3989 0.0321
-0.750 0.4074 0.01186 0.00421 -0.0637 0.3927 0.0327
-0.500 0.4283 0.01189 0.00421 -0.0622 0.3873 0.0329
-0.250 0.4498 0.01191 0.00421 -0.0609 0.3821 0.0335
0.000 0.4705 0.01194 0.00422 -0.0594 0.3764 0.0343
0.250 0.4910 0.01200 0.00425 -0.0579 0.3710 0.0353
0.500 0.5126 0.01204 0.00428 -0.0566 0.3666 0.0364
0.750 0.5332 0.01210 0.00432 -0.0552 0.3617 0.0375
1.000 0.5526 0.01220 0.00439 -0.0535 0.3561 0.0385
1.250 0.5731 0.01226 0.00445 -0.0521 0.3522 0.0402
1.500 0.5940 0.01233 0.00451 -0.0507 0.3479 0.0422
1.750 0.6145 0.01241 0.00459 -0.0493 0.3438 0.0450
2.000 0.6347 0.01251 0.00467 -0.0479 0.3400 0.0497
2.250 0.6544 0.01260 0.00477 -0.0464 0.3361 0.0587
2.500 0.6736 0.01257 0.00487 -0.0447 0.3339 0.1034
2.750 0.6928 0.01260 0.00498 -0.0432 0.3312 0.1359
3.000 0.7121 0.01265 0.00517 -0.0417 0.3284 0.1894
3.250 0.7327 0.01280 0.00532 -0.0404 0.3257 0.2007
3.500 0.7532 0.01295 0.00547 -0.0392 0.3228 0.2068
3.750 0.7734 0.01313 0.00564 -0.0379 0.3195 0.2134
4.000 0.7949 0.01327 0.00579 -0.0369 0.3179 0.2198
4.250 0.8162 0.01341 0.00595 -0.0358 0.3163 0.2246
4.500 0.8370 0.01356 0.00614 -0.0347 0.3146 0.2355
4.750 0.8579 0.01373 0.00631 -0.0337 0.3126 0.2397
5.000 0.8789 0.01391 0.00649 -0.0326 0.3107 0.2436
5.250 0.8992 0.01411 0.00670 -0.0315 0.3083 0.2486
5.500 0.9196 0.01432 0.00691 -0.0305 0.3060 0.2550
5.750 0.9388 0.01457 0.00717 -0.0293 0.3029 0.2599
6.000 0.9589 0.01480 0.00741 -0.0282 0.3011 0.2643
6.250 0.9803 0.01499 0.00762 -0.0274 0.2992 0.2725
6.750 1.0227 0.01540 0.00811 -0.0259 0.2953 0.2988
7.000 1.0438 0.01562 0.00838 -0.0251 0.2935 0.3207
7.250 1.0641 0.01588 0.00871 -0.0243 0.2910 0.3498
7.750 1.2962 0.01619 0.01044 -0.0648 0.2834 0.9952
8.000 1.3333 0.01656 0.01082 -0.0676 0.2822 0.9978
8.250 1.3662 0.01692 0.01118 -0.0696 0.2800 0.9991
8.500 1.3982 0.01729 0.01156 -0.0714 0.2779 0.9999
8.750 1.4163 0.01765 0.01192 -0.0702 0.2757 1.0000
9.000 1.4320 0.01805 0.01231 -0.0687 0.2732 1.0000
9.250 1.4466 0.01850 0.01277 -0.0670 0.2712 1.0000
9.500 1.4611 0.01897 0.01325 -0.0654 0.2690 1.0000
9.750 1.4786 0.01933 0.01363 -0.0642 0.2680 1.0000
10.000 1.4956 0.01971 0.01403 -0.0630 0.2665 1.0000
10.250 1.5115 0.02014 0.01450 -0.0616 0.2650 1.0000
10.500 1.5272 0.02060 0.01498 -0.0603 0.2628 1.0000
10.750 1.5422 0.02111 0.01550 -0.0590 0.2600 1.0000
11.000 1.5563 0.02168 0.01608 -0.0575 0.2579 1.0000
11.250 1.5690 0.02234 0.01675 -0.0560 0.2553 1.0000
11.500 1.5830 0.02295 0.01738 -0.0546 0.2534 1.0000
11.750 1.5982 0.02351 0.01798 -0.0535 0.2519 1.0000
12.000 1.6128 0.02412 0.01863 -0.0523 0.2498 1.0000
12.250 1.6271 0.02476 0.01930 -0.0511 0.2471 1.0000
12.500 1.6380 0.02562 0.02017 -0.0497 0.2433 1.0000
12.750 1.6486 0.02653 0.02108 -0.0482 0.2403 1.0000
13.000 1.6601 0.02741 0.02199 -0.0469 0.2362 1.0000
13.250 1.6666 0.02864 0.02321 -0.0453 0.2275 1.0000
13.500 1.6745 0.02983 0.02441 -0.0438 0.2226 1.0000
13.750 1.6756 0.03152 0.02607 -0.0419 0.2120 1.0000
14.000 1.6715 0.03368 0.02818 -0.0396 0.1988 1.0000
14.250 1.6654 0.03609 0.03056 -0.0375 0.1871 1.0000
14.500 1.6613 0.03844 0.03291 -0.0357 0.1788 1.0000
14.750 1.6517 0.04131 0.03577 -0.0337 0.1700 1.0000
15.000 1.6513 0.04350 0.03799 -0.0325 0.1656 1.0000
15.250 1.6533 0.04552 0.04006 -0.0315 0.1636 1.0000
15.500 1.6420 0.04883 0.04339 -0.0300 0.1571 1.0000
15.750 1.6423 0.05113 0.04575 -0.0293 0.1551 1.0000
16.000 1.6384 0.05389 0.04856 -0.0284 0.1521 1.0000
16.250 1.6352 0.05665 0.05139 -0.0278 0.1502 1.0000
16.500 1.6236 0.06034 0.05512 -0.0270 0.1464 1.0000
16.750 1.6196 0.06328 0.05813 -0.0265 0.1445 1.0000
17.000 1.6172 0.06606 0.06097 -0.0261 0.1426 1.0000
17.250 1.6123 0.06915 0.06413 -0.0258 0.1408 1.0000
17.500 1.6009 0.07302 0.06806 -0.0255 0.1375 1.0000
17.750 1.5894 0.07694 0.07204 -0.0253 0.1351 1.0000
18.000 1.5828 0.08031 0.07547 -0.0251 0.1337 1.0000
18.250 1.5733 0.08408 0.07931 -0.0251 0.1314 1.0000
18.500 1.5676 0.08744 0.08274 -0.0252 0.1298 1.0000
18.750 1.5614 0.09087 0.08624 -0.0254 0.1278 1.0000
19.000 1.5494 0.09509 0.09051 -0.0256 0.1250 1.0000
19.250 1.5392 0.09906 0.09454 -0.0259 0.1229 1.0000
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