FX 66-S-196 AIRFOIL (fx66s196-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-S-196 AIRFOIL (fx66s196-il) Reynolds number: 1,000,000 Max Cl/Cd: 137.43 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66s196-il-1000000.txt Download as CSV file: xf-fx66s196-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: FX 66-S-196 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.6469 0.10633 0.10424 -0.0619 1.0000 0.0091
-17.500 -0.7096 0.09053 0.08813 -0.0705 1.0000 0.0088
-17.250 -0.7045 0.08653 0.08412 -0.0737 0.9994 0.0091
-17.000 -0.7055 0.07793 0.07532 -0.0829 0.9488 0.0092
-16.750 -0.7071 0.06788 0.06498 -0.0955 0.9364 0.0091
-16.500 -0.6837 0.05962 0.05637 -0.1103 0.9116 0.0093
-16.250 -0.6700 0.05520 0.05157 -0.1169 0.8615 0.0095
-16.000 -0.6711 0.05226 0.04840 -0.1182 0.8286 0.0096
-15.750 -0.6781 0.04896 0.04488 -0.1190 0.8076 0.0096
-15.500 -0.6742 0.04690 0.04268 -0.1196 0.7893 0.0099
-15.250 -0.6736 0.04458 0.04021 -0.1200 0.7734 0.0099
-15.000 -0.6765 0.04199 0.03744 -0.1202 0.7609 0.0100
-14.750 -0.6731 0.04011 0.03544 -0.1203 0.7500 0.0101
-14.500 -0.6657 0.03866 0.03386 -0.1204 0.7395 0.0103
-14.250 -0.6610 0.03699 0.03207 -0.1204 0.7305 0.0104
-14.000 -0.6599 0.03509 0.03002 -0.1200 0.7221 0.0107
-13.750 -0.6612 0.03297 0.02777 -0.1191 0.7149 0.0108
-13.500 -0.6583 0.03134 0.02604 -0.1184 0.7078 0.0111
-13.250 -0.6537 0.02981 0.02442 -0.1176 0.7017 0.0112
-13.000 -0.6424 0.02885 0.02343 -0.1173 0.6954 0.0115
-12.750 -0.6333 0.02774 0.02225 -0.1167 0.6899 0.0118
-12.500 -0.6240 0.02660 0.02104 -0.1160 0.6844 0.0119
-12.250 -0.6137 0.02560 0.01997 -0.1153 0.6787 0.0122
-12.000 -0.6026 0.02465 0.01894 -0.1145 0.6736 0.0125
-11.750 -0.5908 0.02374 0.01797 -0.1138 0.6684 0.0128
-11.500 -0.5785 0.02291 0.01707 -0.1130 0.6631 0.0130
-11.250 -0.5681 0.02196 0.01605 -0.1119 0.6585 0.0132
-11.000 -0.5552 0.02117 0.01520 -0.1110 0.6540 0.0134
-10.750 -0.5426 0.02042 0.01437 -0.1100 0.6496 0.0135
-10.500 -0.5374 0.01929 0.01315 -0.1082 0.6451 0.0138
-10.250 -0.5320 0.01819 0.01200 -0.1064 0.6419 0.0140
-10.000 -0.5272 0.01725 0.01102 -0.1043 0.6382 0.0145
-9.750 -0.5232 0.01663 0.01035 -0.1015 0.6346 0.0148
-9.500 -0.5093 0.01620 0.00985 -0.1000 0.6309 0.0152
-9.250 -0.4920 0.01576 0.00938 -0.0989 0.6278 0.0156
-9.000 -0.4737 0.01530 0.00888 -0.0980 0.6250 0.0161
-8.750 -0.4538 0.01489 0.00843 -0.0972 0.6218 0.0166
-8.500 -0.4335 0.01449 0.00796 -0.0965 0.6187 0.0169
-8.250 -0.4124 0.01412 0.00753 -0.0958 0.6157 0.0174
-8.000 -0.3930 0.01358 0.00695 -0.0950 0.6128 0.0185
-7.750 -0.3696 0.01324 0.00659 -0.0947 0.6104 0.0194
-7.500 -0.3454 0.01293 0.00626 -0.0945 0.6078 0.0204
-7.250 -0.3207 0.01266 0.00594 -0.0943 0.6050 0.0214
-7.000 -0.2976 0.01226 0.00549 -0.0939 0.6019 0.0235
-6.750 -0.2729 0.01201 0.00521 -0.0937 0.5986 0.0260
-6.500 -0.2480 0.01166 0.00486 -0.0936 0.5964 0.0305
-6.250 -0.2224 0.01135 0.00457 -0.0936 0.5940 0.0367
-6.000 -0.1968 0.01106 0.00431 -0.0936 0.5917 0.0457
-5.750 -0.1707 0.01081 0.00408 -0.0936 0.5894 0.0570
-5.500 -0.1451 0.01051 0.00385 -0.0937 0.5872 0.0755
-5.250 -0.1195 0.01023 0.00362 -0.0937 0.5849 0.0987
-4.750 -0.0687 0.00946 0.00315 -0.0938 0.5813 0.1831
-4.500 -0.0444 0.00890 0.00286 -0.0938 0.5797 0.2555
-4.250 -0.0219 0.00813 0.00250 -0.0936 0.5780 0.3661
-4.000 0.0018 0.00761 0.00238 -0.0933 0.5764 0.4682
-3.750 0.0311 0.00768 0.00240 -0.0937 0.5747 0.5013
-3.500 0.0601 0.00774 0.00242 -0.0941 0.5731 0.5151
-3.250 0.0888 0.00778 0.00244 -0.0944 0.5714 0.5230
-3.000 0.1179 0.00788 0.00244 -0.0947 0.5696 0.5282
-2.750 0.1464 0.00793 0.00247 -0.0950 0.5675 0.5331
-2.500 0.1756 0.00797 0.00250 -0.0954 0.5665 0.5380
-2.250 0.2049 0.00805 0.00253 -0.0958 0.5655 0.5434
-2.000 0.2336 0.00804 0.00256 -0.0961 0.5643 0.5489
-1.750 0.2627 0.00808 0.00258 -0.0965 0.5630 0.5519
-1.500 0.2918 0.00811 0.00259 -0.0969 0.5616 0.5541
-1.250 0.3208 0.00819 0.00263 -0.0973 0.5602 0.5578
-1.000 0.3495 0.00823 0.00267 -0.0976 0.5589 0.5633
-0.750 0.3784 0.00828 0.00272 -0.0980 0.5576 0.5665
-0.500 0.4072 0.00833 0.00275 -0.0983 0.5564 0.5684
-0.250 0.4361 0.00838 0.00278 -0.0987 0.5551 0.5699
0.000 0.4649 0.00845 0.00281 -0.0991 0.5536 0.5708
0.250 0.4938 0.00855 0.00288 -0.0996 0.5520 0.5718
0.500 0.5227 0.00859 0.00291 -0.1000 0.5510 0.5730
0.750 0.5515 0.00862 0.00294 -0.1004 0.5502 0.5741
1.000 0.5803 0.00865 0.00297 -0.1008 0.5493 0.5747
1.250 0.6091 0.00867 0.00300 -0.1012 0.5483 0.5750
1.500 0.6378 0.00870 0.00303 -0.1016 0.5471 0.5753
1.750 0.6663 0.00872 0.00306 -0.1020 0.5460 0.5757
2.000 0.6948 0.00873 0.00308 -0.1024 0.5448 0.5763
2.250 0.7233 0.00875 0.00311 -0.1027 0.5437 0.5769
2.500 0.7517 0.00878 0.00315 -0.1031 0.5426 0.5775
2.750 0.7800 0.00881 0.00320 -0.1035 0.5414 0.5781
3.000 0.8083 0.00886 0.00325 -0.1038 0.5400 0.5787
3.250 0.8365 0.00893 0.00333 -0.1041 0.5383 0.5794
3.500 0.8651 0.00907 0.00346 -0.1046 0.5363 0.5802
3.750 0.8929 0.00909 0.00353 -0.1048 0.5354 0.5811
4.000 0.9206 0.00912 0.00360 -0.1051 0.5342 0.5818
4.250 0.9483 0.00915 0.00367 -0.1053 0.5327 0.5826
4.500 0.9760 0.00919 0.00375 -0.1056 0.5313 0.5833
4.750 1.0036 0.00923 0.00382 -0.1058 0.5296 0.5841
5.000 1.0310 0.00927 0.00388 -0.1060 0.5277 0.5850
5.250 1.0582 0.00931 0.00394 -0.1061 0.5258 0.5859
5.500 1.0855 0.00940 0.00404 -0.1063 0.5234 0.5871
5.750 1.1134 0.00955 0.00420 -0.1067 0.5210 0.5882
6.000 1.1394 0.00956 0.00427 -0.1066 0.5193 0.5895
6.250 1.1652 0.00957 0.00434 -0.1065 0.5164 0.5905
6.500 1.1909 0.00958 0.00439 -0.1063 0.5132 0.5916
6.750 1.2156 0.00960 0.00444 -0.1060 0.5088 0.5935
7.000 1.2405 0.00968 0.00455 -0.1057 0.5046 0.5953
7.250 1.2647 0.00967 0.00463 -0.1053 0.5005 0.5971
7.500 1.2885 0.00969 0.00470 -0.1048 0.4954 0.5991
7.750 1.3105 0.00975 0.00479 -0.1040 0.4881 0.6013
8.000 1.3342 0.00979 0.00489 -0.1035 0.4811 0.6036
8.250 1.3556 0.00990 0.00502 -0.1026 0.4749 0.6060
8.500 1.3757 0.01001 0.00515 -0.1014 0.4630 0.6087
8.750 1.3886 0.01020 0.00534 -0.0988 0.4490 0.6121
9.000 1.3992 0.01051 0.00564 -0.0959 0.4344 0.6157
9.250 1.4022 0.01109 0.00614 -0.0918 0.4070 0.6197
9.500 1.3888 0.01227 0.00713 -0.0852 0.3705 0.6234
9.750 1.3719 0.01384 0.00855 -0.0790 0.3323 0.6282
10.000 1.3537 0.01589 0.01045 -0.0735 0.2992 0.6333
10.250 1.3417 0.01805 0.01250 -0.0696 0.2701 0.6386
10.500 1.3245 0.02091 0.01525 -0.0659 0.2398 0.6445
10.750 1.3081 0.02406 0.01829 -0.0630 0.2094 0.6510
11.000 1.3024 0.02665 0.02083 -0.0613 0.1905 0.6588
11.250 1.2911 0.02980 0.02391 -0.0594 0.1649 0.6668
11.500 1.2828 0.03286 0.02691 -0.0580 0.1426 0.6762
11.750 1.2751 0.03605 0.03003 -0.0569 0.1199 0.6870
12.000 1.2692 0.03924 0.03316 -0.0562 0.0986 0.6996
12.250 1.2668 0.04232 0.03619 -0.0559 0.0785 0.7143
12.500 1.2675 0.04531 0.03916 -0.0561 0.0622 0.7305
12.750 1.2726 0.04830 0.04215 -0.0571 0.0471 0.7528
13.000 1.2884 0.05110 0.04504 -0.0597 0.0369 0.7913
13.250 1.3165 0.05518 0.04927 -0.0666 0.0231 0.8646
13.500 1.3481 0.05905 0.05329 -0.0732 0.0161 1.0000
13.750 1.3545 0.06122 0.05549 -0.0729 0.0142 1.0000
14.000 1.3572 0.06376 0.05805 -0.0725 0.0124 1.0000
14.250 1.3650 0.06578 0.06011 -0.0722 0.0115 1.0000
14.500 1.3705 0.06808 0.06244 -0.0719 0.0107 1.0000
14.750 1.3736 0.07065 0.06504 -0.0716 0.0099 1.0000
15.000 1.3797 0.07290 0.06734 -0.0714 0.0093 1.0000
15.250 1.3847 0.07532 0.06980 -0.0712 0.0090 1.0000
15.500 1.3909 0.07757 0.07210 -0.0710 0.0086 1.0000
15.750 1.3952 0.08004 0.07461 -0.0709 0.0081 1.0000
16.000 1.3993 0.08261 0.07722 -0.0708 0.0079 1.0000
16.250 1.3958 0.08607 0.08075 -0.0705 0.0073 1.0000
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