FX 66-S-171 AIRFOIL (fx66s171-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-S-171 AIRFOIL (fx66s171-il) Reynolds number: 200,000 Max Cl/Cd: 70.31 at α=10.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66s171-il-200000.txt Download as CSV file: xf-fx66s171-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-171 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.3828 0.05460 0.05065 -0.1083 0.8547 0.0383
-10.250 -0.3926 0.05013 0.04589 -0.1108 0.8226 0.0371
-10.000 -0.4120 0.04684 0.04230 -0.1101 0.8004 0.0361
-9.750 -0.4366 0.04261 0.03761 -0.1081 0.7846 0.0340
-9.500 -0.4581 0.03888 0.03294 -0.1048 0.7722 0.0314
-9.250 -0.4495 0.03667 0.03037 -0.1036 0.7602 0.0313
-9.000 -0.4386 0.03416 0.02752 -0.1024 0.7497 0.0313
-8.500 -0.4083 0.02888 0.02176 -0.1009 0.7316 0.0329
-8.250 -0.3881 0.02783 0.02057 -0.1004 0.7237 0.0345
-8.000 -0.3675 0.02651 0.01905 -0.0996 0.7155 0.0361
-7.750 -0.3455 0.02511 0.01737 -0.0989 0.7092 0.0372
-7.500 -0.3228 0.02399 0.01604 -0.0981 0.7018 0.0387
-7.250 -0.3012 0.02230 0.01425 -0.0973 0.6961 0.0409
-7.000 -0.2792 0.02148 0.01344 -0.0968 0.6900 0.0441
-6.750 -0.2558 0.02090 0.01272 -0.0962 0.6841 0.0484
-6.500 -0.2356 0.01975 0.01156 -0.0953 0.6796 0.0528
-6.250 -0.2126 0.01921 0.01097 -0.0948 0.6739 0.0590
-6.000 -0.1921 0.01829 0.01006 -0.0940 0.6687 0.0664
-5.750 -0.1699 0.01756 0.00928 -0.0935 0.6645 0.0777
-5.500 -0.1479 0.01680 0.00857 -0.0930 0.6599 0.0983
-5.250 -0.1294 0.01539 0.00765 -0.0925 0.6555 0.1814
-5.000 -0.1107 0.01429 0.00733 -0.0919 0.6517 0.3667
-4.750 -0.0840 0.01446 0.00751 -0.0916 0.6484 0.4242
-4.500 -0.0573 0.01470 0.00772 -0.0913 0.6440 0.4537
-4.250 -0.0301 0.01499 0.00788 -0.0910 0.6398 0.4767
-4.000 -0.0026 0.01525 0.00805 -0.0907 0.6361 0.4937
-3.750 0.0253 0.01551 0.00817 -0.0906 0.6332 0.5083
-3.500 0.0520 0.01573 0.00835 -0.0903 0.6293 0.5221
-3.250 0.0788 0.01594 0.00857 -0.0899 0.6255 0.5345
-3.000 0.1060 0.01611 0.00872 -0.0896 0.6221 0.5462
-2.750 0.1338 0.01626 0.00878 -0.0894 0.6194 0.5574
-2.500 0.1618 0.01644 0.00881 -0.0895 0.6168 0.5683
-2.250 0.1880 0.01649 0.00895 -0.0892 0.6133 0.5752
-2.000 0.2156 0.01653 0.00888 -0.0893 0.6098 0.5830
-1.750 0.2433 0.01651 0.00884 -0.0893 0.6068 0.5880
-1.500 0.2716 0.01655 0.00880 -0.0895 0.6044 0.5940
-1.250 0.3006 0.01664 0.00873 -0.0899 0.6022 0.6001
-1.000 0.3268 0.01670 0.00887 -0.0898 0.5993 0.6047
-0.750 0.3539 0.01679 0.00895 -0.0899 0.5962 0.6104
-0.500 0.3817 0.01685 0.00895 -0.0901 0.5933 0.6160
-0.250 0.4095 0.01689 0.00898 -0.0902 0.5906 0.6211
0.000 0.4381 0.01698 0.00897 -0.0905 0.5883 0.6275
0.250 0.4659 0.01712 0.00909 -0.0907 0.5860 0.6327
0.500 0.4915 0.01727 0.00933 -0.0905 0.5830 0.6379
0.750 0.5184 0.01741 0.00945 -0.0907 0.5797 0.6439
1.000 0.5460 0.01743 0.00948 -0.0907 0.5764 0.6490
1.250 0.5746 0.01746 0.00947 -0.0909 0.5737 0.6549
1.500 0.6033 0.01762 0.00956 -0.0913 0.5713 0.6619
1.750 0.6271 0.01781 0.00991 -0.0908 0.5678 0.6685
2.250 0.6798 0.01815 0.01035 -0.0908 0.5620 0.6829
2.500 0.7079 0.01827 0.01046 -0.0910 0.5596 0.6909
2.750 0.7363 0.01836 0.01056 -0.0912 0.5574 0.6981
3.000 0.7619 0.01863 0.01089 -0.0912 0.5545 0.7070
3.250 0.7850 0.01888 0.01130 -0.0907 0.5507 0.7152
3.500 0.8107 0.01906 0.01156 -0.0905 0.5477 0.7258
3.750 0.8377 0.01919 0.01175 -0.0905 0.5451 0.7381
4.000 0.8654 0.01927 0.01190 -0.0906 0.5430 0.7513
4.250 0.8930 0.01945 0.01213 -0.0907 0.5409 0.7668
4.500 0.9112 0.01987 0.01281 -0.0895 0.5367 0.7857
4.750 0.9334 0.02002 0.01315 -0.0886 0.5332 0.8110
5.000 0.9574 0.01998 0.01328 -0.0878 0.5303 0.8536
5.250 0.9989 0.01986 0.01332 -0.0905 0.5280 1.0000
5.500 1.0283 0.02022 0.01365 -0.0914 0.5254 1.0000
5.750 1.0471 0.02087 0.01442 -0.0905 0.5205 1.0000
6.000 1.0728 0.02116 0.01474 -0.0906 0.5170 1.0000
6.250 1.1017 0.02131 0.01489 -0.0910 0.5143 1.0000
6.500 1.1329 0.02143 0.01497 -0.0917 0.5120 1.0000
6.750 1.1501 0.02217 0.01587 -0.0905 0.5076 1.0000
7.000 1.1708 0.02272 0.01652 -0.0898 0.5035 1.0000
7.250 1.1971 0.02296 0.01682 -0.0898 0.5003 1.0000
7.500 1.2279 0.02302 0.01688 -0.0904 0.4978 1.0000
7.750 1.2538 0.02341 0.01732 -0.0904 0.4948 1.0000
8.000 1.2646 0.02436 0.01850 -0.0883 0.4894 1.0000
8.250 1.2889 0.02466 0.01888 -0.0880 0.4858 1.0000
8.500 1.3208 0.02459 0.01883 -0.0887 0.4830 1.0000
8.750 1.3476 0.02479 0.01909 -0.0887 0.4795 1.0000
9.000 1.3565 0.02564 0.02015 -0.0863 0.4734 1.0000
9.250 1.3974 0.02439 0.01886 -0.0876 0.4680 1.0000
9.500 1.4210 0.02297 0.01744 -0.0861 0.4556 1.0000
9.750 1.4416 0.02171 0.01616 -0.0842 0.4419 1.0000
10.000 1.4580 0.02129 0.01580 -0.0821 0.4311 1.0000
10.250 1.4766 0.02100 0.01554 -0.0804 0.4214 1.0000
10.500 1.4814 0.02126 0.01596 -0.0769 0.4104 1.0000
10.750 1.4841 0.02154 0.01634 -0.0730 0.3990 1.0000
11.000 1.4865 0.02196 0.01680 -0.0693 0.3861 1.0000
11.250 1.4845 0.02269 0.01755 -0.0655 0.3702 1.0000
11.500 1.4787 0.02388 0.01873 -0.0618 0.3520 1.0000
11.750 1.4681 0.02568 0.02050 -0.0584 0.3303 1.0000
12.000 1.4519 0.02822 0.02293 -0.0552 0.3072 1.0000
12.250 1.4323 0.03151 0.02615 -0.0528 0.2786 1.0000
12.500 1.4076 0.03559 0.03008 -0.0506 0.2495 1.0000
12.750 1.3804 0.04021 0.03455 -0.0490 0.2191 1.0000
13.000 1.3534 0.04509 0.03928 -0.0477 0.1934 1.0000
13.250 1.3263 0.05028 0.04433 -0.0469 0.1656 1.0000
13.500 1.2990 0.05585 0.04972 -0.0464 0.1376 1.0000
13.750 1.2736 0.06150 0.05518 -0.0463 0.1086 1.0000
14.000 1.2492 0.06729 0.06076 -0.0465 0.0812 1.0000
14.250 1.2294 0.07278 0.06610 -0.0469 0.0631 1.0000
14.500 1.2140 0.07793 0.07117 -0.0473 0.0510 1.0000
14.750 1.2017 0.08281 0.07602 -0.0479 0.0443 1.0000
15.000 1.1968 0.08684 0.08012 -0.0485 0.0398 1.0000
15.250 1.1904 0.09112 0.08442 -0.0492 0.0365 1.0000
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