FX 66-S-196 V1 AIRFOIL (fx66196v-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-196 V1 AIRFOIL (fx66196v-il) Reynolds number: 200,000 Max Cl/Cd: 61.59 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66196v-il-200000-n5.txt Download as CSV file: xf-fx66196v-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-196 V1 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.4467 0.07790 0.07374 -0.0974 0.9010 0.0150
-14.250 -0.4702 0.06808 0.06351 -0.1064 0.8824 0.0149
-14.000 -0.4791 0.06218 0.05732 -0.1117 0.8622 0.0150
-13.750 -0.4866 0.05755 0.05242 -0.1153 0.8443 0.0150
-13.500 -0.4888 0.05410 0.04878 -0.1177 0.8274 0.0153
-13.250 -0.4961 0.05040 0.04480 -0.1194 0.8129 0.0152
-13.000 -0.4993 0.04762 0.04181 -0.1201 0.7989 0.0154
-12.750 -0.4998 0.04535 0.03936 -0.1205 0.7855 0.0156
-12.500 -0.5006 0.04301 0.03683 -0.1206 0.7730 0.0158
-12.250 -0.4989 0.04103 0.03465 -0.1205 0.7613 0.0161
-12.000 -0.4960 0.03923 0.03265 -0.1202 0.7507 0.0165
-11.750 -0.4925 0.03751 0.03073 -0.1197 0.7402 0.0170
-11.500 -0.4870 0.03584 0.02884 -0.1191 0.7305 0.0174
-11.250 -0.4804 0.03434 0.02709 -0.1182 0.7216 0.0181
-11.000 -0.4708 0.03290 0.02543 -0.1174 0.7130 0.0185
-10.750 -0.4594 0.03156 0.02394 -0.1165 0.7055 0.0189
-10.500 -0.4470 0.03041 0.02271 -0.1156 0.6973 0.0193
-10.000 -0.4220 0.02836 0.02048 -0.1138 0.6837 0.0204
-9.750 -0.4091 0.02741 0.01941 -0.1128 0.6773 0.0211
-9.500 -0.3961 0.02647 0.01837 -0.1117 0.6714 0.0217
-9.250 -0.3835 0.02558 0.01736 -0.1105 0.6653 0.0227
-9.000 -0.3720 0.02476 0.01641 -0.1090 0.6601 0.0235
-8.750 -0.3651 0.02393 0.01557 -0.1072 0.6547 0.0245
-8.500 -0.3536 0.02327 0.01485 -0.1058 0.6495 0.0258
-8.250 -0.3398 0.02260 0.01407 -0.1045 0.6448 0.0270
-8.000 -0.3250 0.02192 0.01329 -0.1033 0.6400 0.0284
-7.750 -0.3107 0.02118 0.01248 -0.1021 0.6352 0.0297
-7.500 -0.2944 0.02054 0.01179 -0.1012 0.6310 0.0319
-7.250 -0.2758 0.02002 0.01115 -0.1004 0.6272 0.0346
-7.000 -0.2574 0.01939 0.01048 -0.0997 0.6229 0.0377
-6.750 -0.2374 0.01884 0.00988 -0.0991 0.6189 0.0416
-6.500 -0.2166 0.01831 0.00929 -0.0986 0.6154 0.0472
-6.000 -0.1727 0.01732 0.00824 -0.0980 0.6089 0.0680
-5.750 -0.1506 0.01675 0.00775 -0.0978 0.6055 0.0915
-5.500 -0.1291 0.01607 0.00724 -0.0976 0.6024 0.1362
-5.250 -0.1086 0.01517 0.00667 -0.0975 0.5996 0.2160
-5.000 -0.0890 0.01412 0.00614 -0.0974 0.5972 0.3434
-4.750 -0.0640 0.01402 0.00635 -0.0972 0.5944 0.4430
-4.500 -0.0364 0.01413 0.00640 -0.0973 0.5915 0.4712
-4.250 -0.0084 0.01426 0.00639 -0.0974 0.5888 0.4911
-4.000 0.0194 0.01441 0.00643 -0.0975 0.5863 0.5068
-3.750 0.0471 0.01461 0.00656 -0.0974 0.5841 0.5211
-3.500 0.0749 0.01485 0.00675 -0.0973 0.5822 0.5341
-3.250 0.1026 0.01500 0.00683 -0.0974 0.5801 0.5430
-3.000 0.1305 0.01507 0.00684 -0.0975 0.5777 0.5490
-2.750 0.1587 0.01508 0.00672 -0.0979 0.5755 0.5539
-2.500 0.1866 0.01508 0.00667 -0.0981 0.5733 0.5564
-2.250 0.2147 0.01509 0.00661 -0.0983 0.5711 0.5587
-2.000 0.2430 0.01509 0.00652 -0.0986 0.5692 0.5610
-1.750 0.2715 0.01510 0.00643 -0.0990 0.5675 0.5631
-1.500 0.3002 0.01514 0.00635 -0.0995 0.5659 0.5658
-1.250 0.3281 0.01517 0.00633 -0.0998 0.5641 0.5687
-1.000 0.3559 0.01520 0.00633 -0.1001 0.5622 0.5708
-0.750 0.3837 0.01523 0.00636 -0.1003 0.5604 0.5724
-0.500 0.4115 0.01528 0.00639 -0.1006 0.5587 0.5744
-0.250 0.4395 0.01534 0.00642 -0.1009 0.5571 0.5766
0.000 0.4675 0.01540 0.00645 -0.1012 0.5556 0.5788
0.250 0.4957 0.01546 0.00647 -0.1016 0.5542 0.5810
0.500 0.5240 0.01554 0.00650 -0.1020 0.5529 0.5833
0.750 0.5525 0.01563 0.00653 -0.1024 0.5518 0.5857
1.000 0.5809 0.01573 0.00661 -0.1028 0.5507 0.5875
1.250 0.6081 0.01584 0.00676 -0.1030 0.5494 0.5896
1.500 0.6349 0.01596 0.00694 -0.1032 0.5480 0.5919
1.750 0.6617 0.01609 0.00711 -0.1033 0.5466 0.5945
2.000 0.6886 0.01624 0.00728 -0.1035 0.5451 0.5976
2.250 0.7157 0.01638 0.00744 -0.1037 0.5436 0.6009
2.500 0.7425 0.01651 0.00761 -0.1039 0.5421 0.6036
2.750 0.7695 0.01664 0.00780 -0.1040 0.5408 0.6063
3.000 0.7967 0.01680 0.00799 -0.1043 0.5396 0.6094
3.250 0.8240 0.01696 0.00818 -0.1045 0.5386 0.6129
3.500 0.8516 0.01713 0.00837 -0.1049 0.5376 0.6166
3.750 0.8791 0.01730 0.00859 -0.1051 0.5367 0.6199
4.000 0.9068 0.01747 0.00881 -0.1055 0.5357 0.6235
4.250 0.9329 0.01769 0.00910 -0.1055 0.5345 0.6276
4.500 0.9566 0.01796 0.00948 -0.1052 0.5329 0.6322
4.750 0.9805 0.01822 0.00986 -0.1050 0.5314 0.6363
5.000 1.0044 0.01847 0.01023 -0.1047 0.5297 0.6409
5.250 1.0289 0.01874 0.01061 -0.1045 0.5283 0.6463
5.500 1.0535 0.01901 0.01099 -0.1044 0.5271 0.6516
5.750 1.0781 0.01927 0.01135 -0.1042 0.5258 0.6573
6.000 1.1035 0.01950 0.01168 -0.1042 0.5244 0.6643
6.250 1.1292 0.01972 0.01201 -0.1042 0.5232 0.6711
6.500 1.1551 0.01997 0.01235 -0.1043 0.5221 0.6793
6.750 1.1814 0.02022 0.01272 -0.1044 0.5212 0.6873
7.000 1.2087 0.02048 0.01306 -0.1047 0.5202 0.6967
7.250 1.2242 0.02095 0.01375 -0.1031 0.5180 0.7058
7.500 1.2391 0.02143 0.01442 -0.1015 0.5153 0.7165
7.750 1.2572 0.02180 0.01498 -0.1003 0.5128 0.7287
8.000 1.2775 0.02211 0.01545 -0.0994 0.5107 0.7421
8.250 1.3001 0.02236 0.01585 -0.0989 0.5089 0.7575
8.500 1.3266 0.02247 0.01609 -0.0990 0.5071 0.7760
8.750 1.3580 0.02239 0.01614 -0.0997 0.5052 0.7981
9.000 1.3601 0.02305 0.01707 -0.0959 0.5015 0.8277
9.250 1.3633 0.02350 0.01779 -0.0923 0.4972 0.8764
9.500 1.3975 0.02269 0.01707 -0.0931 0.4914 1.0000
9.750 1.3891 0.02308 0.01755 -0.0876 0.4833 1.0000
10.000 1.3936 0.02280 0.01726 -0.0840 0.4714 1.0000
10.250 1.3893 0.02326 0.01775 -0.0799 0.4583 1.0000
10.500 1.3828 0.02435 0.01888 -0.0763 0.4449 1.0000
10.750 1.3634 0.02691 0.02159 -0.0725 0.4336 1.0000
11.000 1.3433 0.03009 0.02490 -0.0694 0.4217 1.0000
11.250 1.3149 0.03452 0.02946 -0.0666 0.4090 1.0000
11.500 1.3391 0.03394 0.02863 -0.0660 0.3715 1.0000
11.750 1.3302 0.03636 0.03077 -0.0638 0.3338 1.0000
12.000 1.3110 0.03997 0.03417 -0.0615 0.3041 1.0000
12.250 1.2932 0.04379 0.03784 -0.0596 0.2760 1.0000
12.500 1.2749 0.04787 0.04176 -0.0581 0.2505 1.0000
12.750 1.2580 0.05201 0.04576 -0.0568 0.2231 1.0000
13.000 1.2433 0.05611 0.04971 -0.0559 0.1984 1.0000
13.250 1.2300 0.06019 0.05365 -0.0551 0.1710 1.0000
13.500 1.2174 0.06430 0.05759 -0.0545 0.1442 1.0000
13.750 1.2090 0.06805 0.06121 -0.0541 0.1196 1.0000
14.000 1.2008 0.07188 0.06490 -0.0538 0.0954 1.0000
14.250 1.1950 0.07548 0.06836 -0.0537 0.0746 1.0000
14.500 1.1911 0.07893 0.07171 -0.0536 0.0572 1.0000
14.750 1.1892 0.08223 0.07493 -0.0536 0.0451 1.0000
15.250 1.1907 0.08833 0.08102 -0.0538 0.0310 1.0000
15.500 1.1923 0.09135 0.08408 -0.0540 0.0272 1.0000
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Polar graphs
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