GOE 285 AIRFOIL (goe285-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 285 AIRFOIL (goe285-il) Reynolds number: 200,000 Max Cl/Cd: 65.22 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe285-il-200000-n5.txt Download as CSV file: xf-goe285-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 285 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3871 0.08932 0.08546 -0.0368 1.0000 0.0360
-9.000 -0.3938 0.08481 0.08099 -0.0385 1.0000 0.0357
-8.750 -0.4066 0.08006 0.07630 -0.0401 1.0000 0.0353
-8.500 -0.5499 0.04633 0.04208 -0.0590 0.9952 0.0336
-8.250 -0.5329 0.04121 0.03664 -0.0630 0.9884 0.0340
-8.000 -0.5098 0.03736 0.03248 -0.0661 0.9833 0.0346
-7.750 -0.4909 0.03296 0.02759 -0.0681 0.9755 0.0351
-7.500 -0.4676 0.02914 0.02323 -0.0698 0.9694 0.0354
-7.250 -0.4415 0.02660 0.02028 -0.0708 0.9627 0.0359
-7.000 -0.4119 0.02459 0.01790 -0.0721 0.9579 0.0363
-6.750 -0.3852 0.02303 0.01606 -0.0724 0.9501 0.0368
-6.500 -0.3533 0.02163 0.01437 -0.0736 0.9452 0.0373
-6.250 -0.3254 0.02055 0.01306 -0.0738 0.9358 0.0380
-6.000 -0.2919 0.01951 0.01182 -0.0750 0.9293 0.0388
-5.750 -0.2632 0.01867 0.01093 -0.0753 0.9185 0.0395
-5.500 -0.2319 0.01792 0.01011 -0.0760 0.9088 0.0402
-5.250 -0.2006 0.01722 0.00933 -0.0766 0.8985 0.0409
-5.000 -0.1714 0.01659 0.00861 -0.0767 0.8863 0.0416
-4.750 -0.1419 0.01601 0.00794 -0.0768 0.8739 0.0425
-4.500 -0.1128 0.01549 0.00730 -0.0769 0.8615 0.0435
-4.250 -0.0850 0.01503 0.00675 -0.0766 0.8489 0.0445
-4.000 -0.0578 0.01464 0.00635 -0.0764 0.8372 0.0459
-3.750 -0.0301 0.01434 0.00600 -0.0761 0.8263 0.0480
-3.500 -0.0030 0.01404 0.00562 -0.0757 0.8144 0.0505
-3.250 0.0239 0.01377 0.00535 -0.0754 0.8023 0.0532
-3.000 0.0509 0.01353 0.00504 -0.0749 0.7894 0.0574
-2.750 0.0779 0.01332 0.00481 -0.0745 0.7764 0.0638
-2.500 0.1045 0.01313 0.00459 -0.0741 0.7613 0.0728
-2.250 0.1311 0.01296 0.00439 -0.0736 0.7451 0.0827
-2.000 0.1577 0.01283 0.00421 -0.0731 0.7283 0.0925
-1.750 0.1843 0.01274 0.00405 -0.0727 0.7114 0.1014
-1.500 0.2109 0.01264 0.00392 -0.0722 0.6946 0.1109
-1.250 0.2374 0.01257 0.00380 -0.0717 0.6772 0.1213
-1.000 0.2637 0.01251 0.00368 -0.0713 0.6597 0.1331
-0.750 0.2901 0.01246 0.00358 -0.0708 0.6428 0.1479
-0.500 0.3164 0.01236 0.00349 -0.0704 0.6276 0.1668
-0.250 0.3428 0.01225 0.00341 -0.0700 0.6141 0.1930
0.000 0.3686 0.01207 0.00336 -0.0696 0.6003 0.2432
0.250 0.3927 0.01163 0.00334 -0.0690 0.5860 0.3867
0.500 0.4122 0.01087 0.00338 -0.0673 0.5712 0.6385
0.750 0.4537 0.01041 0.00356 -0.0690 0.5523 0.9358
1.000 0.5133 0.01056 0.00356 -0.0756 0.5280 1.0000
1.250 0.5372 0.01071 0.00356 -0.0747 0.5090 1.0000
1.500 0.5609 0.01088 0.00358 -0.0738 0.4909 1.0000
1.750 0.5844 0.01106 0.00362 -0.0728 0.4740 1.0000
2.000 0.6080 0.01126 0.00369 -0.0719 0.4586 1.0000
2.250 0.6317 0.01146 0.00377 -0.0710 0.4447 1.0000
2.500 0.6555 0.01168 0.00388 -0.0702 0.4320 1.0000
3.000 0.7034 0.01212 0.00414 -0.0685 0.4083 1.0000
3.250 0.7276 0.01235 0.00429 -0.0678 0.3974 1.0000
3.500 0.7515 0.01259 0.00446 -0.0670 0.3863 1.0000
3.750 0.7761 0.01280 0.00463 -0.0663 0.3752 1.0000
4.000 0.8003 0.01305 0.00482 -0.0656 0.3647 1.0000
4.250 0.8245 0.01330 0.00501 -0.0649 0.3539 1.0000
4.500 0.8489 0.01354 0.00523 -0.0642 0.3435 1.0000
4.750 0.8728 0.01382 0.00545 -0.0635 0.3340 1.0000
5.000 0.8971 0.01407 0.00568 -0.0628 0.3241 1.0000
5.250 0.9209 0.01436 0.00593 -0.0621 0.3148 1.0000
5.500 0.9445 0.01467 0.00619 -0.0614 0.3052 1.0000
5.750 0.9682 0.01497 0.00646 -0.0607 0.2960 1.0000
6.000 0.9910 0.01532 0.00675 -0.0598 0.2869 1.0000
6.250 1.0147 0.01562 0.00705 -0.0592 0.2783 1.0000
6.750 1.0613 0.01629 0.00771 -0.0577 0.2666 1.0000
7.000 1.0844 0.01663 0.00806 -0.0570 0.2608 1.0000
7.250 1.1067 0.01702 0.00842 -0.0561 0.2553 1.0000
7.500 1.1302 0.01733 0.00880 -0.0555 0.2501 1.0000
7.750 1.1529 0.01768 0.00919 -0.0547 0.2451 1.0000
8.000 1.1741 0.01812 0.00960 -0.0537 0.2401 1.0000
8.250 1.1972 0.01842 0.01000 -0.0530 0.2336 1.0000
8.500 1.2181 0.01884 0.01044 -0.0520 0.2269 1.0000
8.750 1.2394 0.01923 0.01088 -0.0510 0.2212 1.0000
9.000 1.2607 0.01960 0.01133 -0.0501 0.2142 1.0000
9.250 1.2801 0.02006 0.01182 -0.0489 0.2064 1.0000
9.500 1.2997 0.02048 0.01230 -0.0478 0.1950 1.0000
9.750 1.3185 0.02094 0.01280 -0.0465 0.1781 1.0000
10.000 1.3237 0.02205 0.01356 -0.0435 0.1258 1.0000
10.250 1.3282 0.02335 0.01473 -0.0405 0.1056 1.0000
10.500 1.3355 0.02455 0.01590 -0.0380 0.0915 1.0000
10.750 1.3436 0.02571 0.01706 -0.0357 0.0769 1.0000
11.000 1.3494 0.02705 0.01837 -0.0334 0.0623 1.0000
11.250 1.3546 0.02849 0.01979 -0.0313 0.0539 1.0000
11.500 1.3602 0.02996 0.02130 -0.0294 0.0499 1.0000
11.750 1.3646 0.03158 0.02298 -0.0277 0.0472 1.0000
12.000 1.3682 0.03337 0.02485 -0.0262 0.0453 1.0000
12.250 1.3719 0.03524 0.02682 -0.0250 0.0438 1.0000
12.500 1.3740 0.03736 0.02905 -0.0239 0.0425 1.0000
12.750 1.3740 0.03979 0.03158 -0.0230 0.0414 1.0000
13.000 1.3720 0.04257 0.03447 -0.0224 0.0406 1.0000
13.250 1.3676 0.04574 0.03775 -0.0221 0.0398 1.0000
13.500 1.3636 0.04902 0.04114 -0.0221 0.0392 1.0000
13.750 1.3608 0.05229 0.04455 -0.0222 0.0386 1.0000
14.000 1.3565 0.05581 0.04820 -0.0225 0.0380 1.0000
14.250 1.3511 0.05959 0.05211 -0.0230 0.0374 1.0000
14.500 1.3449 0.06356 0.05620 -0.0237 0.0369 1.0000
14.750 1.3381 0.06772 0.06047 -0.0245 0.0363 1.0000
15.000 1.3313 0.07199 0.06486 -0.0254 0.0358 1.0000
15.250 1.3242 0.07636 0.06933 -0.0265 0.0353 1.0000
15.500 1.3174 0.08071 0.07376 -0.0276 0.0349 1.0000
15.750 1.3109 0.08502 0.07814 -0.0287 0.0344 1.0000
16.000 1.3053 0.08913 0.08229 -0.0296 0.0340 1.0000
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