FX 66-S-196 V1 AIRFOIL (fx66196v-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 66-S-196 V1 AIRFOIL (fx66196v-il) Reynolds number: 200,000 Max Cl/Cd: 49.91 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx66196v-il-200000.txt Download as CSV file: xf-fx66196v-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.1550 0.09956 0.09566 -0.1028 0.8314 0.0722
-12.000 -0.3078 0.06523 0.06115 -0.1241 0.8381 0.0428
-11.750 -0.3303 0.05996 0.05571 -0.1260 0.8244 0.0413
-11.500 -0.4276 0.05263 0.04760 -0.1267 0.8097 0.0363
-11.250 -0.4217 0.04880 0.04361 -0.1263 0.7994 0.0353
-11.000 -0.4311 0.04584 0.04047 -0.1251 0.7879 0.0348
-10.750 -0.4437 0.04329 0.03768 -0.1229 0.7773 0.0345
-10.500 -0.4529 0.04104 0.03513 -0.1202 0.7688 0.0342
-10.250 -0.4555 0.03861 0.03243 -0.1181 0.7594 0.0340
-10.000 -0.4523 0.03657 0.03003 -0.1162 0.7522 0.0344
-9.750 -0.4462 0.03498 0.02812 -0.1143 0.7437 0.0352
-9.500 -0.4349 0.03336 0.02612 -0.1129 0.7374 0.0356
-9.250 -0.4213 0.03191 0.02439 -0.1116 0.7295 0.0360
-9.000 -0.4000 0.02930 0.02153 -0.1111 0.7237 0.0365
-8.750 -0.3759 0.02738 0.01956 -0.1110 0.7172 0.0378
-8.500 -0.3538 0.02625 0.01835 -0.1104 0.7108 0.0392
-8.250 -0.3316 0.02536 0.01731 -0.1099 0.7057 0.0411
-8.000 -0.3108 0.02461 0.01646 -0.1091 0.6993 0.0434
-7.750 -0.2886 0.02346 0.01523 -0.1083 0.6942 0.0457
-7.500 -0.2689 0.02253 0.01429 -0.1075 0.6901 0.0484
-7.250 -0.2504 0.02186 0.01362 -0.1064 0.6846 0.0517
-7.000 -0.2324 0.02111 0.01280 -0.1053 0.6799 0.0560
-6.750 -0.2157 0.02031 0.01199 -0.1043 0.6762 0.0616
-6.500 -0.1989 0.01955 0.01121 -0.1032 0.6722 0.0687
-6.250 -0.1813 0.01880 0.01049 -0.1024 0.6678 0.0810
-6.000 -0.1643 0.01782 0.00961 -0.1016 0.6641 0.1080
-5.750 -0.1534 0.01593 0.00847 -0.1010 0.6610 0.2442
-5.500 -0.1369 0.01521 0.00864 -0.1000 0.6579 0.4513
-5.250 -0.1104 0.01565 0.00899 -0.0997 0.6540 0.4923
-5.000 -0.0833 0.01614 0.00942 -0.0993 0.6506 0.5140
-4.750 -0.0555 0.01661 0.00980 -0.0989 0.6476 0.5309
-4.500 -0.0274 0.01707 0.01016 -0.0986 0.6451 0.5451
-4.250 -0.0001 0.01753 0.01054 -0.0982 0.6425 0.5580
-4.000 0.0258 0.01792 0.01090 -0.0978 0.6393 0.5708
-3.750 0.0522 0.01846 0.01149 -0.0969 0.6362 0.5818
-3.500 0.0789 0.01886 0.01188 -0.0962 0.6334 0.5920
-3.250 0.1066 0.01904 0.01190 -0.0963 0.6311 0.6021
-3.000 0.1342 0.01927 0.01211 -0.0959 0.6291 0.6071
-2.750 0.1615 0.01940 0.01216 -0.0960 0.6271 0.6122
-2.500 0.1880 0.01934 0.01200 -0.0966 0.6246 0.6175
-2.250 0.2141 0.01935 0.01200 -0.0966 0.6222 0.6200
-2.000 0.2407 0.01943 0.01205 -0.0966 0.6200 0.6231
-1.750 0.2680 0.01947 0.01205 -0.0969 0.6180 0.6267
-1.500 0.2963 0.01944 0.01191 -0.0975 0.6163 0.6295
-1.250 0.3252 0.01941 0.01175 -0.0984 0.6147 0.6327
-1.000 0.3538 0.01943 0.01168 -0.0990 0.6133 0.6349
-0.750 0.3810 0.01955 0.01178 -0.0993 0.6118 0.6368
-0.500 0.4056 0.01972 0.01199 -0.0993 0.6099 0.6389
-0.250 0.4308 0.01991 0.01220 -0.0994 0.6080 0.6416
0.000 0.4568 0.02007 0.01235 -0.0996 0.6060 0.6445
0.250 0.4837 0.02020 0.01244 -0.1000 0.6040 0.6475
0.500 0.5110 0.02034 0.01253 -0.1006 0.6024 0.6499
0.750 0.5377 0.02049 0.01269 -0.1008 0.6011 0.6519
1.000 0.5647 0.02067 0.01288 -0.1011 0.5999 0.6544
1.250 0.5923 0.02087 0.01307 -0.1015 0.5988 0.6571
1.500 0.6202 0.02111 0.01328 -0.1020 0.5977 0.6598
1.750 0.6460 0.02148 0.01364 -0.1023 0.5965 0.6628
2.000 0.6648 0.02206 0.01430 -0.1017 0.5942 0.6659
2.250 0.6839 0.02263 0.01500 -0.1010 0.5923 0.6682
2.500 0.7041 0.02318 0.01564 -0.1004 0.5903 0.6710
2.750 0.7266 0.02363 0.01613 -0.1001 0.5884 0.6743
3.000 0.7503 0.02406 0.01659 -0.1001 0.5869 0.6780
3.250 0.7748 0.02451 0.01706 -0.1002 0.5857 0.6823
3.500 0.7993 0.02489 0.01750 -0.1001 0.5846 0.6858
3.750 0.8252 0.02524 0.01789 -0.1003 0.5835 0.6900
4.000 0.8534 0.02554 0.01821 -0.1008 0.5824 0.6947
4.250 0.8466 0.02763 0.02049 -0.0970 0.5790 0.6990
4.500 0.7558 0.03397 0.02713 -0.0836 0.5699 0.7017
4.750 0.7887 0.03392 0.02713 -0.0844 0.5690 0.7071
5.000 0.8228 0.03393 0.02715 -0.0856 0.5682 0.7134
5.250 0.8559 0.03390 0.02721 -0.0865 0.5675 0.7190
5.500 0.8965 0.03349 0.02683 -0.0884 0.5670 0.7263
5.750 0.9385 0.03300 0.02640 -0.0903 0.5665 0.7337
6.000 0.6002 0.05779 0.05129 -0.0626 0.5268 0.7312
6.250 0.6265 0.05808 0.05167 -0.0627 0.5243 0.7392
6.500 0.6571 0.05810 0.05177 -0.0630 0.5227 0.7488
6.750 0.6912 0.05779 0.05154 -0.0634 0.5216 0.7606
7.000 0.6698 0.06130 0.05515 -0.0611 0.5100 0.7692
7.250 0.7005 0.06111 0.05507 -0.0612 0.5080 0.7846
7.500 0.7346 0.06063 0.05473 -0.0615 0.5068 0.8054
7.750 0.7177 0.06430 0.05854 -0.0601 0.4958 0.8262
8.000 0.7473 0.06453 0.05901 -0.0608 0.4935 0.8747
8.250 0.7872 0.06420 0.05884 -0.0629 0.4919 1.0000
8.500 0.7809 0.06729 0.06194 -0.0624 0.4819 1.0000
8.750 0.8090 0.06742 0.06208 -0.0628 0.4788 1.0000
9.000 0.8432 0.06694 0.06162 -0.0632 0.4771 1.0000
9.250 0.8796 0.06621 0.06093 -0.0636 0.4760 1.0000
9.500 0.9158 0.06546 0.06024 -0.0640 0.4752 1.0000
9.750 0.9524 0.06466 0.05949 -0.0643 0.4745 1.0000
10.250 1.3928 0.03057 0.02567 -0.0856 0.5039 1.0000
10.500 1.0052 0.06655 0.06156 -0.0633 0.4593 1.0000
10.750 1.3138 0.03752 0.03279 -0.0730 0.4901 1.0000
11.000 1.4293 0.02864 0.02388 -0.0784 0.4774 1.0000
12.000 1.3676 0.03814 0.03376 -0.0659 0.4418 1.0000
12.250 1.3611 0.04052 0.03620 -0.0644 0.4294 1.0000
12.500 1.3078 0.04813 0.04390 -0.0618 0.4154 1.0000
12.750 1.2533 0.05657 0.05239 -0.0600 0.3964 1.0000
13.000 1.2850 0.05524 0.05110 -0.0598 0.3786 1.0000
13.250 1.3510 0.04876 0.04386 -0.0587 0.2967 1.0000
13.500 1.3289 0.05315 0.04795 -0.0571 0.2588 1.0000
13.750 1.3075 0.05783 0.05241 -0.0558 0.2263 1.0000
14.000 1.2840 0.06296 0.05729 -0.0549 0.1909 1.0000
14.250 1.2616 0.06821 0.06228 -0.0542 0.1558 1.0000
14.500 1.2387 0.07367 0.06743 -0.0538 0.1167 1.0000
14.750 1.2176 0.07910 0.07255 -0.0535 0.0813 1.0000
15.000 1.2016 0.08411 0.07734 -0.0534 0.0594 1.0000
15.250 1.1926 0.08838 0.08153 -0.0534 0.0486 1.0000
15.500 1.1865 0.09240 0.08554 -0.0535 0.0428 1.0000
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