FX 66-182 AIRFOIL (fx66182-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: FX 66-182 AIRFOIL (fx66182-il) Reynolds number: 200,000 Max Cl/Cd: 61.81 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66182-il-200000.txt Download as CSV file: xf-fx66182-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-182 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2280 0.10379 0.10006 -0.0912 0.8236 0.0628
-12.000 -0.2198 0.09868 0.09480 -0.0922 0.7989 0.0639
-11.750 -0.2004 0.09757 0.09350 -0.0904 0.7773 0.0654
-11.500 -0.1907 0.09524 0.09104 -0.0906 0.7628 0.0671
-11.250 -0.1879 0.09195 0.08768 -0.0919 0.7524 0.0699
-11.000 -0.1395 0.08100 0.07681 -0.0881 0.7184 0.0787
-10.750 -0.1321 0.07828 0.07404 -0.0882 0.7128 0.0814
-10.500 -0.1395 0.07322 0.06895 -0.0904 0.7096 0.0841
-10.000 -0.3659 0.03720 0.03217 -0.1071 0.7160 0.0407
-9.750 -0.4241 0.04670 0.04118 -0.1084 0.7207 0.0434
-9.500 -0.4477 0.04033 0.03389 -0.1042 0.7158 0.0342
-9.250 -0.4409 0.03750 0.03071 -0.1028 0.7105 0.0343
-9.000 -0.4286 0.03478 0.02781 -0.1020 0.7047 0.0350
-8.750 -0.4106 0.03307 0.02600 -0.1014 0.6991 0.0361
-8.500 -0.3942 0.03107 0.02370 -0.1004 0.6946 0.0366
-8.250 -0.3755 0.02912 0.02147 -0.0995 0.6900 0.0371
-8.000 -0.3544 0.02750 0.01964 -0.0987 0.6853 0.0381
-7.750 -0.3320 0.02615 0.01804 -0.0980 0.6812 0.0398
-7.250 -0.2858 0.02365 0.01529 -0.0970 0.6734 0.0446
-7.000 -0.2627 0.02288 0.01449 -0.0965 0.6691 0.0474
-6.750 -0.2390 0.02229 0.01377 -0.0960 0.6653 0.0504
-6.500 -0.2160 0.02138 0.01277 -0.0953 0.6622 0.0528
-6.250 -0.1956 0.02058 0.01204 -0.0945 0.6587 0.0560
-6.000 -0.1744 0.01998 0.01144 -0.0936 0.6551 0.0586
-5.750 -0.1528 0.01944 0.01082 -0.0928 0.6519 0.0614
-5.500 -0.1327 0.01877 0.01011 -0.0919 0.6491 0.0652
-5.250 -0.1109 0.01827 0.00954 -0.0913 0.6465 0.0724
-5.000 -0.0908 0.01762 0.00896 -0.0905 0.6433 0.0861
-4.750 -0.0817 0.01569 0.00801 -0.0890 0.6400 0.2596
-4.500 -0.0676 0.01482 0.00816 -0.0871 0.6370 0.4863
-4.250 -0.0408 0.01519 0.00847 -0.0866 0.6343 0.5357
-4.000 -0.0131 0.01563 0.00877 -0.0863 0.6319 0.5612
-3.750 0.0139 0.01621 0.00927 -0.0857 0.6295 0.5825
-3.500 0.0396 0.01676 0.00983 -0.0849 0.6264 0.5994
-3.250 0.0658 0.01721 0.01025 -0.0842 0.6232 0.6138
-3.000 0.0922 0.01767 0.01065 -0.0835 0.6203 0.6280
-2.750 0.1187 0.01816 0.01116 -0.0825 0.6180 0.6399
-2.500 0.1453 0.01859 0.01155 -0.0816 0.6159 0.6512
-2.250 0.1709 0.01890 0.01180 -0.0811 0.6137 0.6621
-2.000 0.1958 0.01906 0.01199 -0.0804 0.6106 0.6683
-1.750 0.2224 0.01907 0.01189 -0.0808 0.6076 0.6751
-1.500 0.2486 0.01909 0.01189 -0.0805 0.6050 0.6787
-1.250 0.2759 0.01913 0.01187 -0.0805 0.6028 0.6827
-1.000 0.3041 0.01916 0.01178 -0.0810 0.6009 0.6872
-0.750 0.3329 0.01924 0.01172 -0.0817 0.5991 0.6912
-0.500 0.3565 0.01933 0.01188 -0.0812 0.5962 0.6942
-0.250 0.3817 0.01943 0.01200 -0.0811 0.5932 0.6975
0.000 0.4084 0.01950 0.01204 -0.0812 0.5906 0.7014
0.250 0.4364 0.01958 0.01203 -0.0818 0.5883 0.7056
0.500 0.4638 0.01963 0.01204 -0.0820 0.5864 0.7085
0.750 0.4918 0.01973 0.01211 -0.0822 0.5846 0.7115
1.000 0.5182 0.01996 0.01232 -0.0824 0.5826 0.7147
1.250 0.5411 0.02022 0.01264 -0.0821 0.5795 0.7185
1.500 0.5668 0.02042 0.01284 -0.0823 0.5765 0.7218
1.750 0.5927 0.02053 0.01298 -0.0823 0.5741 0.7243
2.000 0.6194 0.02067 0.01312 -0.0824 0.5720 0.7275
2.250 0.6476 0.02081 0.01323 -0.0828 0.5702 0.7308
2.500 0.6770 0.02097 0.01334 -0.0834 0.5685 0.7341
2.750 0.6989 0.02141 0.01385 -0.0831 0.5654 0.7375
3.000 0.7191 0.02180 0.01436 -0.0823 0.5621 0.7404
3.250 0.7433 0.02208 0.01470 -0.0821 0.5594 0.7437
3.500 0.7705 0.02224 0.01487 -0.0824 0.5571 0.7471
3.750 0.7990 0.02237 0.01499 -0.0829 0.5551 0.7507
4.000 0.8283 0.02252 0.01512 -0.0835 0.5534 0.7542
4.250 0.8523 0.02294 0.01561 -0.0833 0.5514 0.7577
4.500 0.8632 0.02385 0.01674 -0.0814 0.5471 0.7615
4.750 0.8848 0.02432 0.01729 -0.0810 0.5440 0.7655
5.000 0.9117 0.02452 0.01751 -0.0813 0.5417 0.7694
5.250 0.9396 0.02462 0.01767 -0.0815 0.5398 0.7734
5.500 0.9683 0.02479 0.01788 -0.0819 0.5383 0.7784
5.750 0.9986 0.02506 0.01815 -0.0827 0.5369 0.7834
6.000 0.9870 0.02705 0.02048 -0.0781 0.5305 0.7881
6.250 1.0056 0.02764 0.02118 -0.0772 0.5275 0.7935
6.500 1.0340 0.02778 0.02138 -0.0777 0.5255 0.7997
6.750 1.0644 0.02773 0.02140 -0.0782 0.5239 0.8058
7.000 1.0952 0.02781 0.02154 -0.0789 0.5225 0.8137
7.250 1.0458 0.03167 0.02575 -0.0699 0.5133 0.8234
7.500 1.0703 0.03184 0.02603 -0.0697 0.5110 0.8341
7.750 0.9996 0.03663 0.03103 -0.0591 0.5005 0.8542
8.000 1.0651 0.03455 0.02911 -0.0629 0.5018 0.8787
8.250 1.1653 0.03115 0.02585 -0.0717 0.5034 0.9608
8.500 1.0371 0.04027 0.03505 -0.0576 0.4886 1.0000
8.750 1.0923 0.03816 0.03298 -0.0596 0.4882 1.0000
9.000 1.1549 0.03545 0.03033 -0.0623 0.4865 1.0000
9.250 0.9707 0.05368 0.04850 -0.0529 0.4602 1.0000
9.500 1.0208 0.05106 0.04594 -0.0532 0.4605 1.0000
9.750 1.0739 0.04767 0.04264 -0.0535 0.4601 1.0000
10.000 1.1252 0.04418 0.03923 -0.0535 0.4583 1.0000
10.250 1.0766 0.05166 0.04672 -0.0516 0.4447 1.0000
10.500 1.1258 0.04801 0.04316 -0.0513 0.4415 1.0000
10.750 1.0514 0.05876 0.05389 -0.0496 0.4236 1.0000
11.000 1.4377 0.02326 0.01831 -0.0635 0.4237 1.0000
11.250 1.4392 0.02394 0.01907 -0.0604 0.4130 1.0000
11.500 1.4343 0.02511 0.02030 -0.0572 0.3991 1.0000
11.750 1.4260 0.02685 0.02207 -0.0543 0.3833 1.0000
12.000 1.4158 0.02905 0.02426 -0.0518 0.3635 1.0000
12.250 1.4018 0.03185 0.02701 -0.0496 0.3393 1.0000
12.500 1.3836 0.03520 0.03022 -0.0475 0.3107 1.0000
12.750 1.3599 0.03925 0.03410 -0.0455 0.2784 1.0000
13.000 1.3329 0.04381 0.03846 -0.0437 0.2493 1.0000
13.250 1.3081 0.04849 0.04298 -0.0424 0.2221 1.0000
13.500 1.2820 0.05358 0.04788 -0.0414 0.1929 1.0000
13.750 1.2572 0.05882 0.05293 -0.0408 0.1628 1.0000
14.000 1.2347 0.06407 0.05798 -0.0406 0.1332 1.0000
14.250 1.2119 0.06955 0.06322 -0.0405 0.1009 1.0000
14.500 1.1932 0.07477 0.06822 -0.0406 0.0746 1.0000
14.750 1.1766 0.07990 0.07318 -0.0409 0.0563 1.0000
15.000 1.1662 0.08442 0.07763 -0.0413 0.0471 1.0000
15.250 1.1622 0.08821 0.08145 -0.0417 0.0417 1.0000
15.500 1.1565 0.09227 0.08551 -0.0422 0.0385 1.0000
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