FX 66-S-196 AIRFOIL (fx66s196-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 66-S-196 AIRFOIL (fx66s196-il) Reynolds number: 100,000 Max Cl/Cd: 20 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx66s196-il-100000-n5.txt Download as CSV file: xf-fx66s196-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.2661 0.10210 0.09676 -0.0922 0.8289 0.0313
-13.250 -0.3083 0.08695 0.08157 -0.1005 0.8256 0.0304
-13.000 -0.3815 0.07129 0.06559 -0.1106 0.8216 0.0287
-12.750 -0.4087 0.06522 0.05924 -0.1139 0.8129 0.0286
-12.500 -0.4346 0.05989 0.05361 -0.1160 0.8040 0.0284
-12.250 -0.4449 0.05662 0.05013 -0.1170 0.7952 0.0286
-12.000 -0.4545 0.05351 0.04679 -0.1174 0.7868 0.0290
-11.750 -0.4626 0.05063 0.04368 -0.1175 0.7788 0.0293
-11.500 -0.4686 0.04793 0.04072 -0.1171 0.7715 0.0295
-11.250 -0.4713 0.04549 0.03801 -0.1165 0.7645 0.0298
-11.000 -0.4708 0.04326 0.03552 -0.1156 0.7579 0.0303
-10.750 -0.4663 0.04124 0.03321 -0.1147 0.7525 0.0307
-10.500 -0.4587 0.03931 0.03103 -0.1137 0.7462 0.0315
-10.250 -0.4465 0.03756 0.02899 -0.1128 0.7411 0.0322
-10.000 -0.4338 0.03608 0.02719 -0.1118 0.7364 0.0335
-9.750 -0.4165 0.03477 0.02588 -0.1113 0.7310 0.0349
-9.500 -0.4009 0.03375 0.02479 -0.1106 0.7263 0.0363
-9.250 -0.3818 0.03268 0.02354 -0.1099 0.7226 0.0379
-9.000 -0.3606 0.03162 0.02236 -0.1093 0.7178 0.0398
-8.750 -0.3395 0.03070 0.02128 -0.1085 0.7135 0.0415
-8.500 -0.3247 0.02977 0.02038 -0.1073 0.7096 0.0435
-8.250 -0.3119 0.02905 0.01960 -0.1059 0.7061 0.0468
-8.000 -0.2979 0.02842 0.01887 -0.1044 0.7014 0.0502
-7.750 -0.2863 0.02760 0.01804 -0.1028 0.6974 0.0535
-7.500 -0.2734 0.02689 0.01728 -0.1014 0.6940 0.0579
-7.250 -0.2594 0.02621 0.01652 -0.1000 0.6912 0.0642
-7.000 -0.2464 0.02563 0.01596 -0.0986 0.6873 0.0725
-6.750 -0.2332 0.02499 0.01537 -0.0972 0.6837 0.0838
-6.500 -0.2196 0.02431 0.01473 -0.0958 0.6807 0.1009
-6.250 -0.2062 0.02352 0.01406 -0.0946 0.6781 0.1281
-6.000 -0.1935 0.02260 0.01334 -0.0934 0.6757 0.1775
-5.750 -0.1847 0.02153 0.01273 -0.0920 0.6720 0.2535
-5.500 -0.1742 0.02064 0.01255 -0.0903 0.6686 0.3734
-5.250 -0.1506 0.02161 0.01399 -0.0880 0.6657 0.4800
-5.000 -0.1265 0.02162 0.01365 -0.0882 0.6631 0.5241
-4.750 -0.1001 0.02201 0.01384 -0.0877 0.6611 0.5454
-4.500 -0.0759 0.02260 0.01433 -0.0868 0.6583 0.5622
-4.250 -0.0522 0.02306 0.01468 -0.0859 0.6551 0.5769
-4.000 -0.0279 0.02348 0.01500 -0.0851 0.6523 0.5908
-3.750 -0.0021 0.02404 0.01552 -0.0838 0.6498 0.6008
-3.500 0.0235 0.02429 0.01564 -0.0832 0.6477 0.6112
-3.250 0.0500 0.02445 0.01565 -0.0829 0.6459 0.6192
-3.000 0.0739 0.02460 0.01571 -0.0824 0.6437 0.6262
-2.750 0.0960 0.02483 0.01590 -0.0817 0.6408 0.6308
-2.500 0.1195 0.02485 0.01581 -0.0816 0.6380 0.6357
-2.250 0.1443 0.02480 0.01564 -0.0818 0.6355 0.6406
-2.000 0.1700 0.02485 0.01560 -0.0815 0.6334 0.6435
-1.750 0.1967 0.02482 0.01546 -0.0817 0.6316 0.6463
-1.500 0.2242 0.02475 0.01527 -0.0822 0.6302 0.6492
-1.250 0.2488 0.02481 0.01523 -0.0824 0.6282 0.6519
-1.000 0.2689 0.02505 0.01543 -0.0822 0.6252 0.6552
-0.750 0.2902 0.02530 0.01568 -0.0817 0.6227 0.6571
-0.500 0.3132 0.02550 0.01585 -0.0815 0.6205 0.6589
-0.250 0.3378 0.02563 0.01593 -0.0815 0.6186 0.6606
0.000 0.3643 0.02570 0.01593 -0.0818 0.6168 0.6625
0.250 0.3920 0.02573 0.01588 -0.0822 0.6153 0.6648
0.500 0.4208 0.02574 0.01581 -0.0829 0.6140 0.6675
0.750 0.4324 0.02649 0.01661 -0.0815 0.6102 0.6703
1.000 0.4472 0.02712 0.01729 -0.0803 0.6071 0.6723
1.250 0.4662 0.02758 0.01777 -0.0796 0.6046 0.6742
1.500 0.4884 0.02791 0.01810 -0.0793 0.6027 0.6762
1.750 0.5129 0.02816 0.01834 -0.0793 0.6012 0.6783
2.000 0.5397 0.02834 0.01849 -0.0796 0.5999 0.6809
2.250 0.5686 0.02843 0.01855 -0.0802 0.5987 0.6832
2.500 0.5410 0.03102 0.02131 -0.0742 0.5906 0.6852
2.750 0.5572 0.03172 0.02201 -0.0734 0.5880 0.6872
3.000 0.5805 0.03203 0.02233 -0.0732 0.5862 0.6887
3.250 0.6079 0.03216 0.02247 -0.0735 0.5848 0.6903
3.500 0.6366 0.03226 0.02259 -0.0740 0.5837 0.6922
4.000 0.5330 0.04179 0.03232 -0.0602 0.5605 0.6966
4.250 0.5470 0.04287 0.03342 -0.0596 0.5568 0.6990
4.500 0.5703 0.04336 0.03392 -0.0597 0.5549 0.7016
4.750 0.5958 0.04371 0.03428 -0.0599 0.5535 0.7041
5.000 0.6223 0.04395 0.03457 -0.0600 0.5525 0.7065
5.250 0.6501 0.04411 0.03478 -0.0603 0.5516 0.7091
5.750 0.6448 0.04869 0.03946 -0.0571 0.5377 0.7153
6.000 0.6765 0.04858 0.03938 -0.0577 0.5367 0.7191
6.500 0.6766 0.05294 0.04391 -0.0553 0.5235 0.7257
6.750 0.7056 0.05304 0.04408 -0.0556 0.5222 0.7304
7.250 0.7109 0.05722 0.04843 -0.0539 0.5092 0.7393
7.500 0.7376 0.05751 0.04882 -0.0542 0.5075 0.7449
7.750 0.7678 0.05752 0.04892 -0.0546 0.5063 0.7514
8.250 0.7822 0.06073 0.05236 -0.0533 0.4924 0.7647
8.500 0.8131 0.06052 0.05228 -0.0537 0.4910 0.7736
9.000 0.8275 0.06396 0.05600 -0.0527 0.4773 0.7947
9.250 0.8565 0.06385 0.05609 -0.0529 0.4759 0.8121
9.500 0.8464 0.06707 0.05947 -0.0519 0.4644 0.8319
9.750 0.8798 0.06640 0.05909 -0.0525 0.4623 0.8830
10.250 0.9000 0.06867 0.06154 -0.0514 0.4485 1.0000
10.500 0.9310 0.06828 0.06125 -0.0517 0.4468 1.0000
10.750 0.9248 0.07131 0.06435 -0.0512 0.4346 1.0000
11.000 0.9566 0.07057 0.06371 -0.0513 0.4324 1.0000
11.250 0.9523 0.07349 0.06671 -0.0508 0.4203 1.0000
11.500 0.9829 0.07276 0.06611 -0.0508 0.4177 1.0000
12.500 1.0307 0.07702 0.07079 -0.0495 0.3798 1.0000
12.750 1.0636 0.07530 0.06921 -0.0491 0.3736 1.0000
13.250 1.0861 0.07767 0.07178 -0.0485 0.3452 1.0000
13.500 1.1119 0.07687 0.07100 -0.0481 0.3274 1.0000
13.750 1.1287 0.07730 0.07140 -0.0476 0.3024 1.0000
14.000 1.1499 0.07699 0.07091 -0.0470 0.2685 1.0000
14.250 1.1580 0.07846 0.07213 -0.0464 0.2328 1.0000
14.500 1.1560 0.08139 0.07479 -0.0460 0.1986 1.0000
14.750 1.1496 0.08507 0.07824 -0.0459 0.1658 1.0000
15.000 1.1421 0.08903 0.08199 -0.0460 0.1379 1.0000
15.250 1.1345 0.09316 0.08590 -0.0463 0.1113 1.0000
15.500 1.1294 0.09705 0.08967 -0.0467 0.0896 1.0000
15.750 1.1247 0.10095 0.09343 -0.0472 0.0737 1.0000
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