GOE 385 AIRFOIL (goe385-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 385 AIRFOIL (goe385-il) Reynolds number: 200,000 Max Cl/Cd: 73.03 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe385-il-200000.txt Download as CSV file: xf-goe385-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 385 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3476 0.08901 0.08573 -0.0269 1.0000 0.0359
-7.750 -0.3462 0.08598 0.08275 -0.0282 1.0000 0.0367
-7.500 -0.3472 0.08303 0.07986 -0.0297 1.0000 0.0375
-7.250 -0.3481 0.07998 0.07688 -0.0315 1.0000 0.0384
-7.000 -0.3521 0.07723 0.07417 -0.0327 1.0000 0.0394
-6.750 -0.2844 0.05780 0.05488 -0.0495 0.9857 0.0427
-6.500 -0.2635 0.05349 0.05060 -0.0497 0.9820 0.0441
-6.250 -0.2407 0.04878 0.04585 -0.0538 0.9755 0.0459
-6.000 -0.2124 0.04316 0.04012 -0.0606 0.9712 0.0487
-5.750 -0.1748 0.03856 0.03484 -0.0703 0.9600 0.0536
-5.500 -0.1600 0.03134 0.02774 -0.0726 0.9535 0.0555
-5.250 -0.1360 0.02831 0.02473 -0.0740 0.9442 0.0586
-5.000 -0.1024 0.02678 0.02250 -0.0761 0.9293 0.0672
-4.750 -0.0897 0.02119 0.01696 -0.0769 0.9176 0.0695
-4.500 -0.0703 0.01894 0.01470 -0.0766 0.9038 0.0725
-4.250 -0.0464 0.01679 0.01200 -0.0764 0.8885 0.0834
-4.000 -0.0281 0.01466 0.00997 -0.0760 0.8755 0.0875
-3.750 -0.0057 0.01293 0.00786 -0.0755 0.8611 0.0998
-3.500 0.0159 0.01160 0.00647 -0.0749 0.8478 0.1074
-3.250 0.0381 0.01021 0.00488 -0.0745 0.8349 0.1204
-3.000 0.0611 0.00917 0.00363 -0.0740 0.8223 0.1382
-2.750 0.0826 0.00811 0.00245 -0.0736 0.8093 0.1643
-2.500 0.1113 0.02202 0.01599 -0.0775 0.8237 0.1939
-2.250 0.1348 0.02086 0.01473 -0.0769 0.8079 0.2243
-2.000 0.1833 0.01768 0.01002 -0.0742 0.7960 0.0741
-1.750 0.2111 0.01676 0.00882 -0.0735 0.7823 0.0718
-1.500 0.2393 0.01619 0.00802 -0.0729 0.7700 0.0690
-1.250 0.2671 0.01582 0.00753 -0.0725 0.7586 0.0678
-1.000 0.2946 0.01527 0.00686 -0.0720 0.7481 0.0674
-0.750 0.3218 0.01458 0.00614 -0.0717 0.7373 0.0675
-0.500 0.3487 0.01387 0.00544 -0.0713 0.7264 0.0687
-0.250 0.3756 0.01337 0.00495 -0.0711 0.7163 0.0724
0.000 0.4028 0.01307 0.00460 -0.0708 0.7064 0.0750
0.250 0.4305 0.01284 0.00434 -0.0706 0.6956 0.0780
0.750 0.4859 0.01254 0.00387 -0.0702 0.6760 0.0967
1.000 0.5144 0.01016 0.00384 -0.0700 0.6655 1.0000
1.250 0.5416 0.01030 0.00380 -0.0697 0.6551 1.0000
1.500 0.5687 0.01047 0.00379 -0.0695 0.6454 1.0000
1.750 0.5958 0.01062 0.00383 -0.0693 0.6345 1.0000
2.000 0.6228 0.01078 0.00391 -0.0691 0.6235 1.0000
2.250 0.6498 0.01096 0.00399 -0.0688 0.6125 1.0000
2.500 0.6768 0.01115 0.00406 -0.0686 0.6013 1.0000
2.750 0.7036 0.01129 0.00416 -0.0684 0.5884 1.0000
3.000 0.7304 0.01143 0.00426 -0.0681 0.5750 1.0000
3.250 0.7570 0.01157 0.00436 -0.0679 0.5609 1.0000
3.500 0.7836 0.01170 0.00444 -0.0676 0.5461 1.0000
3.750 0.8101 0.01183 0.00453 -0.0673 0.5303 1.0000
4.000 0.8364 0.01197 0.00463 -0.0670 0.5135 1.0000
4.250 0.8625 0.01214 0.00473 -0.0667 0.4954 1.0000
4.500 0.8885 0.01233 0.00489 -0.0664 0.4764 1.0000
4.750 0.9143 0.01259 0.00507 -0.0661 0.4590 1.0000
5.000 0.9399 0.01289 0.00532 -0.0658 0.4430 1.0000
5.250 0.9655 0.01322 0.00559 -0.0655 0.4283 1.0000
5.500 0.9909 0.01357 0.00589 -0.0652 0.4141 1.0000
5.750 1.0161 0.01392 0.00621 -0.0649 0.4000 1.0000
6.000 1.0412 0.01429 0.00655 -0.0645 0.3872 1.0000
6.250 1.0664 0.01469 0.00692 -0.0642 0.3765 1.0000
6.500 1.0914 0.01509 0.00730 -0.0639 0.3665 1.0000
6.750 1.1165 0.01545 0.00774 -0.0636 0.3560 1.0000
7.000 1.1411 0.01587 0.00816 -0.0633 0.3461 1.0000
7.250 1.1651 0.01628 0.00855 -0.0628 0.3349 1.0000
7.500 1.1886 0.01664 0.00894 -0.0623 0.3221 1.0000
7.750 1.2120 0.01698 0.00938 -0.0618 0.3096 1.0000
8.000 1.2352 0.01734 0.00982 -0.0612 0.2977 1.0000
8.250 1.2578 0.01771 0.01027 -0.0606 0.2850 1.0000
8.500 1.2800 0.01809 0.01071 -0.0599 0.2712 1.0000
8.750 1.3016 0.01847 0.01119 -0.0592 0.2561 1.0000
9.000 1.3226 0.01891 0.01169 -0.0583 0.2388 1.0000
9.250 1.3420 0.01943 0.01223 -0.0573 0.2144 1.0000
9.500 1.3569 0.02031 0.01295 -0.0558 0.1687 1.0000
9.750 1.3585 0.02233 0.01451 -0.0528 0.1104 1.0000
10.000 1.3516 0.02494 0.01664 -0.0488 0.0538 1.0000
10.250 1.3482 0.02685 0.01858 -0.0449 0.0424 1.0000
10.500 1.3503 0.02850 0.02033 -0.0420 0.0370 1.0000
10.750 1.3492 0.03051 0.02243 -0.0394 0.0342 1.0000
11.000 1.3520 0.03235 0.02442 -0.0375 0.0322 1.0000
11.250 1.3535 0.03446 0.02665 -0.0360 0.0305 1.0000
11.500 1.3529 0.03690 0.02920 -0.0347 0.0290 1.0000
11.750 1.3467 0.04005 0.03243 -0.0337 0.0279 1.0000
12.000 1.3425 0.04317 0.03566 -0.0330 0.0270 1.0000
12.250 1.3420 0.04602 0.03866 -0.0325 0.0262 1.0000
12.500 1.3402 0.04909 0.04185 -0.0321 0.0256 1.0000
12.750 1.3384 0.05220 0.04507 -0.0317 0.0250 1.0000
13.000 1.3369 0.05528 0.04826 -0.0314 0.0245 1.0000
13.250 1.3361 0.05829 0.05136 -0.0310 0.0240 1.0000
13.500 1.3361 0.06119 0.05434 -0.0305 0.0235 1.0000
13.750 1.3371 0.06397 0.05719 -0.0298 0.0231 1.0000
14.000 1.3395 0.06656 0.05985 -0.0290 0.0227 1.0000
14.250 1.3429 0.06906 0.06241 -0.0280 0.0223 1.0000
14.500 1.3479 0.07144 0.06487 -0.0265 0.0218 1.0000
14.750 1.3517 0.07432 0.06788 -0.0249 0.0213 1.0000
15.000 1.3483 0.07802 0.07179 -0.0255 0.0211 1.0000
15.250 1.3442 0.08195 0.07592 -0.0261 0.0208 1.0000
15.500 1.3391 0.08613 0.08031 -0.0268 0.0207 1.0000
15.750 1.3324 0.09068 0.08508 -0.0277 0.0206 1.0000
16.000 1.3240 0.09559 0.09019 -0.0290 0.0206 1.0000
16.250 1.3134 0.10099 0.09581 -0.0309 0.0206 1.0000
16.500 1.3015 0.10678 0.10181 -0.0332 0.0207 1.0000
16.750 1.2881 0.11304 0.10828 -0.0360 0.0208 1.0000
17.000 1.2738 0.11967 0.11510 -0.0393 0.0209 1.0000
17.250 1.2586 0.12675 0.12238 -0.0432 0.0210 1.0000
17.500 1.2429 0.13424 0.13005 -0.0475 0.0211 1.0000
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