FX 61-163 AIRFOIL (fx61163-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 61-163 AIRFOIL (fx61163-il) Reynolds number: 50,000 Max Cl/Cd: 19.36 at α=11.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx61163-il-50000-n5.txt Download as CSV file: xf-fx61163-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-163 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4019 0.10472 0.09779 -0.0500 1.0001 0.0396
-11.000 -0.4087 0.09834 0.09147 -0.0534 1.0001 0.0390
-10.750 -0.4212 0.09160 0.08480 -0.0572 1.0001 0.0382
-10.500 -0.4404 0.08485 0.07806 -0.0612 1.0001 0.0372
-10.250 -0.4631 0.07891 0.07211 -0.0641 1.0001 0.0364
-10.000 -0.4882 0.07392 0.06706 -0.0657 1.0001 0.0356
-9.750 -0.5139 0.07000 0.06308 -0.0656 1.0001 0.0351
-9.500 -0.5407 0.06707 0.06009 -0.0637 1.0001 0.0346
-9.250 -0.5633 0.06443 0.05738 -0.0616 1.0001 0.0343
-9.000 -0.5801 0.06212 0.05500 -0.0591 1.0001 0.0343
-8.750 -0.5965 0.06031 0.05313 -0.0559 1.0001 0.0343
-8.500 -0.5945 0.05763 0.05029 -0.0561 0.9932 0.0348
-8.250 -0.5718 0.05392 0.04627 -0.0599 0.9771 0.0360
-8.000 -0.5477 0.05039 0.04233 -0.0631 0.9615 0.0373
-7.750 -0.5210 0.04703 0.03847 -0.0656 0.9475 0.0385
-7.500 -0.4912 0.04394 0.03491 -0.0675 0.9350 0.0393
-7.250 -0.4579 0.04120 0.03176 -0.0690 0.9244 0.0402
-7.000 -0.4176 0.03880 0.02897 -0.0706 0.9175 0.0416
-6.750 -0.3791 0.03708 0.02699 -0.0709 0.9084 0.0436
-6.500 -0.3378 0.03559 0.02548 -0.0720 0.9024 0.0487
-6.250 -0.3035 0.03460 0.02426 -0.0718 0.8922 0.0540
-6.000 -0.2750 0.03332 0.02297 -0.0720 0.8822 0.0596
-5.750 -0.2479 0.03199 0.02153 -0.0728 0.8726 0.0701
-5.500 -0.2297 0.03062 0.02018 -0.0728 0.8607 0.0846
-5.250 -0.2158 0.02878 0.01864 -0.0729 0.8495 0.1192
-5.000 -0.2167 0.02631 0.01844 -0.0701 0.8397 0.4048
-4.750 -0.1933 0.02987 0.02216 -0.0633 0.8309 0.5870
-4.500 -0.1630 0.03426 0.02629 -0.0553 0.8244 0.6493
-4.250 -0.1376 0.03471 0.02642 -0.0537 0.8162 0.6664
-4.000 -0.1128 0.03451 0.02588 -0.0535 0.8090 0.6766
-3.750 -0.0927 0.03421 0.02530 -0.0532 0.8010 0.6876
-3.500 -0.0653 0.03407 0.02489 -0.0528 0.7947 0.6944
-3.250 -0.0464 0.03383 0.02444 -0.0523 0.7869 0.7037
-3.000 -0.0174 0.03360 0.02393 -0.0525 0.7818 0.7110
-2.750 -0.0010 0.03349 0.02368 -0.0515 0.7738 0.7192
-2.500 0.0258 0.03327 0.02324 -0.0517 0.7683 0.7260
-2.250 0.0440 0.03314 0.02298 -0.0510 0.7612 0.7334
-2.000 0.0680 0.03302 0.02268 -0.0507 0.7554 0.7394
-1.750 0.0913 0.03281 0.02230 -0.0510 0.7499 0.7469
-1.500 0.1103 0.03283 0.02224 -0.0498 0.7429 0.7521
-1.250 0.1362 0.03264 0.02187 -0.0504 0.7380 0.7589
-1.000 0.1541 0.03269 0.02185 -0.0494 0.7313 0.7640
-0.750 0.1768 0.03265 0.02171 -0.0491 0.7255 0.7693
-0.500 0.2057 0.03246 0.02138 -0.0502 0.7214 0.7755
-0.250 0.2183 0.03271 0.02162 -0.0483 0.7137 0.7798
0.000 0.2441 0.03265 0.02147 -0.0485 0.7087 0.7849
0.250 0.2654 0.03277 0.02152 -0.0486 0.7028 0.7905
0.500 0.2842 0.03292 0.02164 -0.0476 0.6963 0.7947
0.750 0.3131 0.03283 0.02147 -0.0481 0.6921 0.7995
1.000 0.3280 0.03323 0.02188 -0.0475 0.6843 0.8050
1.250 0.3516 0.03326 0.02188 -0.0470 0.6790 0.8089
1.500 0.3736 0.03344 0.02203 -0.0467 0.6734 0.8135
1.750 0.3931 0.03381 0.02241 -0.0466 0.6662 0.8185
2.000 0.4221 0.03376 0.02233 -0.0470 0.6620 0.8223
2.250 0.4334 0.03439 0.02303 -0.0456 0.6538 0.8269
2.500 0.4612 0.03452 0.02315 -0.0462 0.6486 0.8314
2.750 0.4818 0.03496 0.02362 -0.0461 0.6422 0.8357
3.000 0.5002 0.03536 0.02407 -0.0453 0.6352 0.8399
3.250 0.5327 0.03529 0.02401 -0.0462 0.6313 0.8440
3.500 0.5436 0.03633 0.02514 -0.0456 0.6216 0.8488
3.750 0.5724 0.03626 0.02510 -0.0456 0.6171 0.8526
4.000 0.5817 0.03728 0.02624 -0.0444 0.6077 0.8574
4.250 0.6129 0.03734 0.02635 -0.0453 0.6027 0.8616
4.500 0.6228 0.03840 0.02752 -0.0442 0.5936 0.8661
4.750 0.6494 0.03854 0.02773 -0.0443 0.5881 0.8705
5.000 0.6614 0.03969 0.02901 -0.0437 0.5790 0.8753
5.250 0.6882 0.03994 0.02935 -0.0440 0.5733 0.8795
5.500 0.6959 0.04119 0.03072 -0.0429 0.5637 0.8845
5.750 0.7241 0.04134 0.03098 -0.0432 0.5581 0.8892
6.000 0.7287 0.04286 0.03265 -0.0421 0.5475 0.8943
6.250 0.7594 0.04267 0.03258 -0.0422 0.5426 0.8990
6.500 0.7616 0.04451 0.03456 -0.0412 0.5311 0.9048
6.750 0.7954 0.04403 0.03421 -0.0414 0.5269 0.9098
7.000 0.7949 0.04623 0.03658 -0.0406 0.5148 0.9163
7.250 0.8327 0.04544 0.03594 -0.0409 0.5113 0.9218
7.500 0.8303 0.04782 0.03847 -0.0401 0.4986 0.9293
8.000 0.8592 0.04987 0.04085 -0.0396 0.4797 0.9460
8.250 0.8736 0.05092 0.04209 -0.0396 0.4695 0.9570
8.750 0.9202 0.05145 0.04299 -0.0400 0.4531 0.9999
9.250 0.9383 0.05603 0.04790 -0.0420 0.4273 0.9999
9.750 0.9980 0.05551 0.04780 -0.0427 0.4102 0.9999
10.000 1.0073 0.05763 0.05010 -0.0434 0.3971 0.9999
10.250 1.0193 0.05942 0.05206 -0.0439 0.3843 0.9999
10.500 1.0372 0.06036 0.05318 -0.0442 0.3723 0.9999
11.000 1.1078 0.05755 0.05082 -0.0435 0.3510 0.9999
11.250 1.1257 0.05815 0.05157 -0.0434 0.3362 0.9999
11.500 1.1346 0.05981 0.05334 -0.0435 0.3197 0.9999
11.750 1.1369 0.06231 0.05596 -0.0437 0.3024 0.9999
12.000 1.1451 0.06406 0.05781 -0.0437 0.2853 0.9999
12.250 1.1543 0.06575 0.05963 -0.0437 0.2690 0.9999
12.500 1.1628 0.06752 0.06147 -0.0436 0.2529 0.9999
12.750 1.1721 0.06901 0.06297 -0.0433 0.2358 0.9999
13.000 1.1726 0.07172 0.06565 -0.0434 0.2183 0.9999
13.250 1.1680 0.07524 0.06920 -0.0439 0.2013 0.9999
13.500 1.1647 0.07865 0.07259 -0.0445 0.1849 0.9999
13.750 1.1610 0.08220 0.07609 -0.0451 0.1693 0.9999
14.000 1.1569 0.08597 0.07985 -0.0459 0.1553 0.9999
14.250 1.1530 0.08983 0.08371 -0.0468 0.1426 0.9999
14.500 1.1497 0.09371 0.08758 -0.0477 0.1311 0.9999
14.750 1.1471 0.09747 0.09129 -0.0487 0.1206 0.9999
15.000 1.1444 0.10141 0.09526 -0.0497 0.1110 0.9999
15.250 1.1399 0.10586 0.09982 -0.0512 0.1024 0.9999
15.500 1.1387 0.10962 0.10358 -0.0523 0.0947 0.9999
15.750 1.1355 0.11404 0.10814 -0.0539 0.0878 0.9999
16.000 1.1365 0.11754 0.11162 -0.0549 0.0821 0.9999
16.250 1.1309 0.12273 0.11704 -0.0570 0.0770 0.9999
16.500 1.1351 0.12548 0.11965 -0.0580 0.0715 0.9999
16.750 1.1246 0.13208 0.12657 -0.0613 0.0682 0.9999
17.000 1.1171 0.13810 0.13280 -0.0643 0.0651 0.9999
17.250 1.1290 0.13916 0.13365 -0.0643 0.0601 0.9999
17.500 1.1124 0.14773 0.14256 -0.0694 0.0588 0.9999
17.750 1.0920 0.15780 0.15288 -0.0756 0.0581 0.9999
18.000 1.0646 0.17085 0.16609 -0.0839 0.0583 0.9999
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