S2027 (s2027-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: S2027 (s2027-il) Reynolds number: 50,000 Max Cl/Cd: 28.36 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s2027-il-50000-n5.txt Download as CSV file: xf-s2027-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: S2027
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3942 0.10333 0.09636 -0.0417 1.0000 0.0500
-10.750 -0.4000 0.09761 0.09072 -0.0446 1.0000 0.0493
-10.500 -0.4104 0.09072 0.08391 -0.0486 1.0000 0.0485
-10.250 -0.4390 0.08008 0.07331 -0.0561 1.0000 0.0468
-9.750 -0.5213 0.06572 0.05871 -0.0659 1.0000 0.0447
-9.500 -0.5427 0.06310 0.05607 -0.0641 1.0000 0.0446
-9.250 -0.5623 0.06071 0.05362 -0.0615 1.0000 0.0445
-9.000 -0.5807 0.05863 0.05145 -0.0582 1.0000 0.0445
-8.750 -0.5980 0.05660 0.04929 -0.0546 1.0000 0.0445
-8.500 -0.6121 0.05454 0.04706 -0.0511 1.0000 0.0445
-8.250 -0.6223 0.05240 0.04470 -0.0479 1.0000 0.0445
-8.000 -0.6175 0.04941 0.04131 -0.0474 0.9954 0.0449
-7.750 -0.5930 0.04630 0.03800 -0.0498 0.9862 0.0463
-7.500 -0.5665 0.04390 0.03538 -0.0520 0.9770 0.0487
-7.250 -0.5372 0.04133 0.03242 -0.0541 0.9688 0.0510
-7.000 -0.5083 0.03890 0.02956 -0.0555 0.9599 0.0528
-6.750 -0.4759 0.03672 0.02697 -0.0568 0.9521 0.0547
-6.500 -0.4422 0.03484 0.02487 -0.0582 0.9448 0.0569
-6.250 -0.4112 0.03340 0.02337 -0.0592 0.9366 0.0601
-6.000 -0.3763 0.03210 0.02184 -0.0608 0.9293 0.0671
-5.750 -0.3495 0.03088 0.02064 -0.0614 0.9199 0.0748
-5.500 -0.3171 0.02949 0.01917 -0.0627 0.9128 0.0869
-5.250 -0.2958 0.02828 0.01801 -0.0623 0.9020 0.1089
-4.750 -0.2525 0.02517 0.01618 -0.0629 0.8838 0.2935
-4.500 -0.2346 0.02463 0.01611 -0.0614 0.8730 0.3960
-4.250 -0.2109 0.02455 0.01620 -0.0601 0.8643 0.4737
-4.000 -0.1870 0.02464 0.01626 -0.0587 0.8551 0.5287
-3.750 -0.1652 0.02481 0.01636 -0.0569 0.8452 0.5680
-3.500 -0.1368 0.02487 0.01626 -0.0561 0.8379 0.6049
-3.250 -0.1167 0.02503 0.01630 -0.0541 0.8273 0.6326
-3.000 -0.0909 0.02510 0.01625 -0.0528 0.8192 0.6589
-2.750 -0.0671 0.02514 0.01614 -0.0515 0.8101 0.6834
-2.500 -0.0444 0.02521 0.01609 -0.0499 0.8009 0.7047
-2.250 -0.0174 0.02515 0.01587 -0.0491 0.7934 0.7269
-2.000 0.0035 0.02522 0.01585 -0.0474 0.7834 0.7458
-1.750 0.0332 0.02510 0.01559 -0.0469 0.7770 0.7647
-1.500 0.0530 0.02519 0.01558 -0.0452 0.7665 0.7829
-1.250 0.0790 0.02513 0.01540 -0.0444 0.7587 0.8014
-1.000 0.1035 0.02511 0.01529 -0.0435 0.7499 0.8198
-0.750 0.1292 0.02514 0.01522 -0.0428 0.7411 0.8372
-0.500 0.1603 0.02505 0.01503 -0.0429 0.7337 0.8546
-0.250 0.1881 0.02512 0.01503 -0.0429 0.7243 0.8726
0.000 0.2256 0.02498 0.01476 -0.0442 0.7176 0.8898
0.250 0.2577 0.02510 0.01482 -0.0453 0.7077 0.9083
0.500 0.3020 0.02490 0.01449 -0.0479 0.7016 0.9243
0.750 0.3405 0.02507 0.01460 -0.0506 0.6911 0.9417
1.000 0.3864 0.02501 0.01446 -0.0542 0.6831 0.9572
1.250 0.4330 0.02496 0.01434 -0.0581 0.6743 0.9727
1.500 0.4769 0.02503 0.01435 -0.0619 0.6646 0.9905
1.750 0.5070 0.02493 0.01417 -0.0628 0.6573 1.0000
2.000 0.5112 0.02533 0.01453 -0.0598 0.6468 1.0000
2.250 0.5270 0.02545 0.01456 -0.0580 0.6392 1.0000
2.500 0.5413 0.02578 0.01483 -0.0563 0.6298 1.0000
2.750 0.5584 0.02614 0.01513 -0.0550 0.6207 1.0000
3.000 0.5828 0.02625 0.01516 -0.0544 0.6132 1.0000
3.250 0.5998 0.02678 0.01566 -0.0532 0.6032 1.0000
3.500 0.6290 0.02675 0.01558 -0.0530 0.5968 1.0000
3.750 0.6451 0.02741 0.01625 -0.0518 0.5862 1.0000
4.000 0.6689 0.02771 0.01652 -0.0512 0.5780 1.0000
4.250 0.6921 0.02804 0.01687 -0.0506 0.5694 1.0000
4.500 0.7118 0.02860 0.01745 -0.0497 0.5600 1.0000
4.750 0.7402 0.02869 0.01751 -0.0496 0.5529 1.0000
5.000 0.7567 0.02945 0.01833 -0.0484 0.5427 1.0000
5.250 0.7865 0.02948 0.01837 -0.0483 0.5359 1.0000
5.500 0.8027 0.03028 0.01924 -0.0472 0.5256 1.0000
5.750 0.8236 0.03083 0.01984 -0.0464 0.5168 1.0000
6.000 0.8493 0.03110 0.02015 -0.0460 0.5089 1.0000
6.250 0.8647 0.03198 0.02115 -0.0448 0.4990 1.0000
6.500 0.8966 0.03190 0.02109 -0.0448 0.4923 1.0000
6.750 0.9072 0.03306 0.02238 -0.0433 0.4817 1.0000
7.000 0.9291 0.03357 0.02296 -0.0426 0.4734 1.0000
7.250 0.9505 0.03410 0.02360 -0.0418 0.4647 1.0000
7.500 0.9632 0.03515 0.02477 -0.0404 0.4551 1.0000
7.750 0.9948 0.03508 0.02475 -0.0403 0.4480 1.0000
8.000 0.9997 0.03657 0.02640 -0.0384 0.4375 1.0000
8.250 1.0216 0.03706 0.02698 -0.0376 0.4294 1.0000
8.500 1.0382 0.03784 0.02790 -0.0364 0.4203 1.0000
8.750 1.0444 0.03925 0.02945 -0.0346 0.4108 1.0000
9.000 1.0793 0.03891 0.02920 -0.0347 0.4033 1.0000
9.250 1.0692 0.04115 0.03158 -0.0316 0.3931 1.0000
9.500 1.0860 0.04185 0.03239 -0.0304 0.3846 1.0000
9.750 1.1004 0.04266 0.03336 -0.0291 0.3756 1.0000
10.000 1.0916 0.04516 0.03598 -0.0269 0.3659 1.0000
10.250 1.1294 0.04433 0.03525 -0.0266 0.3578 1.0000
10.500 1.1113 0.04762 0.03869 -0.0244 0.3477 1.0000
10.750 1.1078 0.05006 0.04125 -0.0231 0.3380 1.0000
11.000 1.1527 0.04816 0.03945 -0.0224 0.3290 1.0000
11.250 1.1185 0.05345 0.04488 -0.0211 0.3186 1.0000
11.500 1.1116 0.05651 0.04806 -0.0204 0.3084 1.0000
11.750 1.1432 0.05524 0.04693 -0.0191 0.2984 1.0000
12.000 1.1361 0.05829 0.05010 -0.0185 0.2876 1.0000
12.250 1.1087 0.06419 0.05612 -0.0191 0.2770 1.0000
12.500 1.1157 0.06577 0.05781 -0.0185 0.2664 1.0000
12.750 1.1374 0.06524 0.05737 -0.0172 0.2550 1.0000
13.000 1.1311 0.06861 0.06085 -0.0174 0.2439 1.0000
13.250 1.1013 0.07585 0.06820 -0.0193 0.2335 1.0000
13.500 1.0997 0.07883 0.07128 -0.0196 0.2223 1.0000
13.750 1.1095 0.07992 0.07245 -0.0191 0.2106 1.0000
14.000 1.1179 0.08123 0.07381 -0.0188 0.1983 1.0000
14.250 1.1228 0.08312 0.07577 -0.0188 0.1858 1.0000
14.500 1.0934 0.09147 0.08424 -0.0219 0.1764 1.0000
14.750 1.0880 0.09559 0.08846 -0.0232 0.1654 1.0000
15.000 1.0904 0.09828 0.09118 -0.0237 0.1540 1.0000
15.250 1.0942 0.10072 0.09361 -0.0242 0.1425 1.0000
15.500 1.0994 0.10288 0.09570 -0.0246 0.1312 1.0000
15.750 1.0783 0.11079 0.10380 -0.0281 0.1239 1.0000
16.000 1.0772 0.11447 0.10747 -0.0294 0.1144 1.0000
16.250 1.0840 0.11646 0.10935 -0.0299 0.1048 1.0000
16.500 1.0635 0.12487 0.11797 -0.0340 0.0993 1.0000
16.750 1.0685 0.12738 0.12040 -0.0349 0.0911 1.0000
17.000 1.0488 0.13608 0.12928 -0.0394 0.0867 1.0000
17.250 1.0577 0.13770 0.13080 -0.0400 0.0793 1.0000
17.500 1.0293 0.14931 0.14261 -0.0464 0.0771 1.0000
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