FX 61-168 AIRFOIL (fx61168-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 61-168 AIRFOIL (fx61168-il) Reynolds number: 100,000 Max Cl/Cd: 44.66 at α=11.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx61168-il-100000.txt Download as CSV file: xf-fx61168-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 61-168 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3495 0.09962 0.09534 -0.0486 1.0000 0.1500
-9.500 -0.3513 0.09672 0.09253 -0.0475 1.0000 0.1587
-9.250 -0.3670 0.09390 0.08986 -0.0475 1.0000 0.1657
-9.000 -0.4139 0.09152 0.08776 -0.0465 1.0000 0.1672
-8.750 -0.4071 0.09190 0.08825 -0.0407 0.9983 0.1734
-7.750 -0.4693 0.04915 0.04337 -0.0866 0.9252 0.0830
-7.500 -0.4335 0.04337 0.03668 -0.0891 0.9199 0.0647
-7.250 -0.4083 0.03960 0.03256 -0.0901 0.9098 0.0626
-7.000 -0.3681 0.03539 0.02778 -0.0928 0.9058 0.0586
-6.750 -0.3368 0.03273 0.02463 -0.0934 0.8971 0.0574
-6.500 -0.2926 0.03023 0.02188 -0.0959 0.8926 0.0583
-6.250 -0.2501 0.02847 0.01995 -0.0983 0.8876 0.0635
-6.000 -0.2159 0.02720 0.01847 -0.0987 0.8793 0.0665
-5.750 -0.1740 0.02514 0.01667 -0.1003 0.8754 0.0735
-5.500 -0.1514 0.02430 0.01587 -0.0993 0.8661 0.0827
-5.250 -0.1200 0.02292 0.01458 -0.1005 0.8603 0.1000
-5.000 -0.1089 0.02158 0.01356 -0.0990 0.8502 0.1452
-4.750 -0.0952 0.02183 0.01607 -0.0943 0.8442 0.5942
-4.500 -0.0791 0.02441 0.01854 -0.0883 0.8353 0.6240
-4.250 -0.0423 0.02832 0.02233 -0.0818 0.8310 0.6541
-4.000 0.0251 0.03187 0.02561 -0.0790 0.8288 0.6851
-3.750 0.0293 0.03191 0.02557 -0.0756 0.8195 0.6982
-3.500 0.0747 0.03172 0.02514 -0.0777 0.8149 0.7050
-3.250 0.0812 0.03160 0.02493 -0.0748 0.8073 0.7155
-3.000 0.0944 0.03132 0.02451 -0.0737 0.8007 0.7274
-2.750 0.1347 0.03114 0.02416 -0.0749 0.7961 0.7330
-2.500 0.1314 0.03111 0.02411 -0.0708 0.7881 0.7437
-2.250 0.1708 0.03085 0.02366 -0.0724 0.7838 0.7503
-2.000 0.1674 0.03090 0.02371 -0.0681 0.7767 0.7596
-1.750 0.1918 0.03077 0.02348 -0.0676 0.7712 0.7665
-1.500 0.2185 0.03043 0.02299 -0.0682 0.7671 0.7747
-1.250 0.2129 0.03076 0.02337 -0.0630 0.7592 0.7814
-1.000 0.2321 0.03052 0.02303 -0.0625 0.7542 0.7892
-0.750 0.2519 0.03053 0.02298 -0.0612 0.7488 0.7953
-0.500 0.2479 0.03075 0.02320 -0.0570 0.7414 0.8039
-0.250 0.2872 0.03040 0.02274 -0.0587 0.7377 0.8099
0.000 0.2687 0.03097 0.02336 -0.0527 0.7290 0.8177
0.250 0.2956 0.03078 0.02312 -0.0525 0.7243 0.8224
0.500 0.3365 0.03038 0.02260 -0.0550 0.7211 0.8276
0.750 0.3084 0.03133 0.02363 -0.0477 0.7110 0.8339
1.000 0.3452 0.03097 0.02320 -0.0491 0.7074 0.8383
1.250 0.3337 0.03183 0.02412 -0.0444 0.6986 0.8441
1.500 0.3592 0.03179 0.02404 -0.0448 0.6935 0.8488
1.750 0.4032 0.03128 0.02345 -0.0471 0.6907 0.8526
2.000 0.3798 0.03265 0.02490 -0.0411 0.6796 0.8583
2.250 0.4255 0.03220 0.02439 -0.0443 0.6764 0.8625
2.500 0.4036 0.03360 0.02587 -0.0383 0.6653 0.8672
2.750 0.4480 0.03306 0.02529 -0.0407 0.6618 0.8710
3.000 0.5017 0.03236 0.02453 -0.0446 0.6596 0.8750
3.250 0.4763 0.03413 0.02640 -0.0387 0.6471 0.8798
3.500 0.4618 0.03575 0.02809 -0.0345 0.6363 0.8846
3.750 0.5033 0.03536 0.02769 -0.0366 0.6322 0.8886
4.000 0.5583 0.03458 0.02691 -0.0403 0.6300 0.8920
4.250 0.5284 0.03691 0.02932 -0.0345 0.6170 0.8970
4.500 0.5797 0.03594 0.02836 -0.0372 0.6148 0.9005
4.750 0.6409 0.03484 0.02725 -0.0413 0.6132 0.9040
5.000 0.5546 0.04071 0.03326 -0.0319 0.5900 0.9107
5.250 0.5947 0.03993 0.03251 -0.0329 0.5861 0.9146
5.500 0.6482 0.03849 0.03112 -0.0351 0.5843 0.9184
5.750 0.7058 0.03696 0.02961 -0.0379 0.5829 0.9218
6.000 0.6237 0.04417 0.03694 -0.0315 0.5584 0.9294
6.250 0.6674 0.04315 0.03597 -0.0326 0.5552 0.9338
6.500 0.6869 0.04370 0.03661 -0.0322 0.5486 0.9392
6.750 0.7572 0.04053 0.03351 -0.0344 0.5503 0.9432
7.000 0.8447 0.03697 0.03002 -0.0393 0.5517 0.9459
7.250 0.8017 0.04107 0.03424 -0.0341 0.5349 0.9555
7.500 0.8914 0.03706 0.03033 -0.0387 0.5361 0.9589
7.750 0.8034 0.04585 0.03924 -0.0339 0.5098 0.9746
8.000 0.8694 0.04275 0.03629 -0.0359 0.5091 0.9856
8.250 0.9541 0.03851 0.03217 -0.0395 0.5087 1.0000
8.500 1.0564 0.03412 0.02788 -0.0462 0.5070 1.0000
8.750 1.0474 0.03614 0.03005 -0.0437 0.4946 1.0000
9.000 1.0550 0.03758 0.03163 -0.0431 0.4835 1.0000
9.250 1.1563 0.03299 0.02714 -0.0496 0.4789 1.0000
9.500 1.1733 0.03340 0.02771 -0.0492 0.4674 1.0000
9.750 1.2195 0.03229 0.02672 -0.0514 0.4571 1.0000
10.000 1.2719 0.03078 0.02528 -0.0543 0.4449 1.0000
10.250 1.3048 0.03017 0.02473 -0.0551 0.4303 1.0000
10.500 1.3286 0.03006 0.02469 -0.0549 0.4144 1.0000
10.750 1.3457 0.03026 0.02496 -0.0541 0.3969 1.0000
11.000 1.3615 0.03057 0.02532 -0.0533 0.3780 1.0000
11.250 1.3791 0.03088 0.02556 -0.0526 0.3579 1.0000
11.500 1.3795 0.03233 0.02710 -0.0509 0.3394 1.0000
11.750 1.3809 0.03395 0.02878 -0.0495 0.3207 1.0000
12.000 1.3825 0.03569 0.03051 -0.0484 0.3017 1.0000
12.250 1.3833 0.03767 0.03243 -0.0475 0.2828 1.0000
12.500 1.3783 0.04031 0.03511 -0.0468 0.2645 1.0000
12.750 1.3733 0.04310 0.03790 -0.0462 0.2462 1.0000
13.000 1.3685 0.04600 0.04072 -0.0457 0.2283 1.0000
13.250 1.3632 0.04907 0.04368 -0.0454 0.2108 1.0000
13.500 1.3545 0.05267 0.04732 -0.0453 0.1937 1.0000
13.750 1.3460 0.05637 0.05097 -0.0454 0.1770 1.0000
14.000 1.3373 0.06024 0.05478 -0.0456 0.1607 1.0000
14.250 1.3286 0.06426 0.05874 -0.0459 0.1457 1.0000
14.500 1.3212 0.06828 0.06270 -0.0464 0.1318 1.0000
14.750 1.3158 0.07222 0.06659 -0.0469 0.1193 1.0000
15.000 1.3112 0.07615 0.07049 -0.0476 0.1084 1.0000
15.250 1.3076 0.07998 0.07425 -0.0485 0.0990 1.0000
15.500 1.3017 0.08436 0.07871 -0.0498 0.0909 1.0000
15.750 1.2986 0.08841 0.08282 -0.0509 0.0833 1.0000
16.000 1.2965 0.09222 0.08655 -0.0520 0.0763 1.0000
16.250 1.2902 0.09703 0.09157 -0.0538 0.0702 1.0000
16.500 1.2887 0.10081 0.09521 -0.0551 0.0637 1.0000
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