FX 60-160 AIRFOIL (fx60160-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 60-160 AIRFOIL (fx60160-il) Reynolds number: 100,000 Max Cl/Cd: 51.02 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx60160-il-100000.txt Download as CSV file: xf-fx60160-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: FX 60-160 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3652 0.11544 0.11055 -0.0468 1.0000 0.1433
-10.500 -0.3982 0.11331 0.10857 -0.0479 1.0000 0.1493
-10.250 -0.4595 0.11128 0.10679 -0.0496 1.0000 0.1504
-10.000 -0.3911 0.10869 0.10404 -0.0425 1.0000 0.1577
-9.750 -0.4096 0.10711 0.10256 -0.0406 1.0000 0.1628
-9.500 -0.4629 0.10554 0.10120 -0.0403 1.0000 0.1658
-9.250 -0.4481 0.10329 0.09896 -0.0362 1.0000 0.1704
-9.000 -0.4496 0.10227 0.09797 -0.0330 1.0000 0.1761
-8.750 -0.4902 0.10024 0.09609 -0.0323 1.0000 0.1809
-8.500 -0.4733 0.09726 0.09310 -0.0319 0.9978 0.1886
-8.250 -0.4817 0.09215 0.08803 -0.0382 0.9911 0.2015
-7.000 -0.5588 0.04853 0.04178 -0.0706 0.9438 0.1025
-6.750 -0.5293 0.04462 0.03752 -0.0729 0.9404 0.0996
-6.500 -0.5148 0.04227 0.03483 -0.0718 0.9338 0.0986
-6.250 -0.4873 0.03952 0.03160 -0.0727 0.9289 0.0961
-6.000 -0.4516 0.03718 0.02877 -0.0746 0.9255 0.0951
-5.750 -0.4327 0.03597 0.02736 -0.0736 0.9194 0.0965
-5.500 -0.4048 0.03474 0.02588 -0.0741 0.9143 0.0988
-5.250 -0.3678 0.03337 0.02426 -0.0758 0.9108 0.1003
-5.000 -0.3445 0.03252 0.02324 -0.0751 0.9053 0.1019
-4.750 -0.3189 0.03176 0.02233 -0.0750 0.8999 0.1051
-4.500 -0.2845 0.03065 0.02135 -0.0764 0.8962 0.1099
-4.250 -0.2592 0.03009 0.02080 -0.0761 0.8911 0.1138
-4.000 -0.2381 0.02972 0.02038 -0.0751 0.8850 0.1184
-3.750 -0.2060 0.02895 0.01980 -0.0762 0.8811 0.1279
-3.500 -0.1834 0.02856 0.01944 -0.0757 0.8756 0.1376
-3.250 -0.1626 0.02816 0.01907 -0.0750 0.8694 0.1519
-3.000 -0.1350 0.02579 0.01812 -0.0769 0.8657 0.3728
-2.750 -0.1295 0.02693 0.02021 -0.0708 0.8586 0.6142
-2.500 -0.1092 0.02822 0.02139 -0.0679 0.8524 0.6568
-2.250 -0.0785 0.02921 0.02235 -0.0662 0.8487 0.6822
-2.000 -0.0762 0.03005 0.02317 -0.0614 0.8399 0.6990
-1.750 -0.0521 0.03068 0.02374 -0.0591 0.8351 0.7231
-1.500 -0.0386 0.03122 0.02425 -0.0557 0.8287 0.7400
-1.250 -0.0257 0.03159 0.02461 -0.0523 0.8218 0.7570
-1.000 0.0006 0.03170 0.02466 -0.0503 0.8179 0.7780
-0.750 0.0022 0.03208 0.02503 -0.0461 0.8089 0.7914
-0.500 0.0278 0.03200 0.02487 -0.0452 0.8039 0.8054
-0.250 0.0707 0.03169 0.02443 -0.0477 0.8010 0.8156
0.000 0.0679 0.03215 0.02488 -0.0435 0.7903 0.8231
0.250 0.1067 0.03187 0.02450 -0.0455 0.7865 0.8317
0.500 0.1119 0.03228 0.02490 -0.0425 0.7771 0.8405
0.750 0.1422 0.03208 0.02464 -0.0429 0.7720 0.8497
1.000 0.1844 0.03169 0.02418 -0.0450 0.7692 0.8587
1.250 0.1825 0.03233 0.02483 -0.0413 0.7577 0.8662
1.500 0.2239 0.03198 0.02442 -0.0435 0.7543 0.8732
1.750 0.2292 0.03261 0.02506 -0.0410 0.7436 0.8802
2.000 0.2670 0.03233 0.02474 -0.0427 0.7393 0.8868
2.250 0.3081 0.03199 0.02438 -0.0447 0.7359 0.8931
2.500 0.3130 0.03277 0.02517 -0.0424 0.7245 0.9007
2.750 0.3586 0.03227 0.02466 -0.0450 0.7218 0.9069
3.000 0.3618 0.03330 0.02573 -0.0427 0.7097 0.9154
3.250 0.4072 0.03280 0.02524 -0.0452 0.7067 0.9222
3.500 0.4563 0.03216 0.02464 -0.0482 0.7045 0.9288
3.750 0.4643 0.03343 0.02598 -0.0471 0.6916 0.9396
4.000 0.4882 0.03443 0.02705 -0.0484 0.6817 0.9508
4.250 0.5377 0.03425 0.02695 -0.0523 0.6770 0.9616
4.500 0.5967 0.03346 0.02624 -0.0570 0.6749 0.9749
4.750 0.6569 0.03237 0.02523 -0.0615 0.6735 1.0000
5.000 0.6497 0.03438 0.02726 -0.0588 0.6595 1.0000
5.250 0.6537 0.03616 0.02907 -0.0576 0.6470 1.0000
5.500 0.7008 0.03539 0.02837 -0.0600 0.6442 1.0000
5.750 0.7543 0.03428 0.02735 -0.0631 0.6427 1.0000
6.000 0.8177 0.03257 0.02575 -0.0672 0.6408 1.0000
6.250 0.8255 0.03353 0.02677 -0.0653 0.6279 1.0000
6.750 0.9958 0.02589 0.01933 -0.0768 0.6115 1.0000
7.000 1.0291 0.02496 0.01846 -0.0770 0.5973 1.0000
7.250 1.0618 0.02413 0.01771 -0.0771 0.5827 1.0000
7.500 1.0947 0.02320 0.01682 -0.0772 0.5660 1.0000
7.750 1.1223 0.02250 0.01614 -0.0764 0.5468 1.0000
8.000 1.1297 0.02249 0.01621 -0.0728 0.5255 1.0000
8.250 1.1383 0.02231 0.01598 -0.0691 0.4972 1.0000
8.500 1.1415 0.02258 0.01620 -0.0650 0.4646 1.0000
8.750 1.1388 0.02326 0.01668 -0.0602 0.4201 1.0000
9.000 1.1271 0.02466 0.01773 -0.0549 0.3551 1.0000
9.250 1.1062 0.02705 0.01951 -0.0493 0.2632 1.0000
9.500 1.0827 0.03026 0.02205 -0.0447 0.1896 1.0000
9.750 1.0705 0.03315 0.02458 -0.0416 0.1559 1.0000
10.000 1.0662 0.03561 0.02688 -0.0393 0.1405 1.0000
10.250 1.0671 0.03776 0.02898 -0.0376 0.1313 1.0000
10.500 1.0689 0.03986 0.03102 -0.0359 0.1250 1.0000
10.750 1.0774 0.04149 0.03266 -0.0346 0.1195 1.0000
11.000 1.0885 0.04295 0.03409 -0.0334 0.1143 1.0000
11.250 1.1085 0.04396 0.03492 -0.0324 0.1096 1.0000
11.500 1.1346 0.04471 0.03574 -0.0318 0.1060 1.0000
11.750 1.1680 0.04536 0.03637 -0.0316 0.1025 1.0000
12.000 1.2343 0.04606 0.03680 -0.0341 0.0968 1.0000
12.250 1.2636 0.04752 0.03852 -0.0341 0.0945 1.0000
12.500 1.2906 0.04926 0.04045 -0.0342 0.0908 1.0000
12.750 1.3347 0.05213 0.04322 -0.0365 0.0832 1.0000
13.000 1.3299 0.05391 0.04532 -0.0338 0.0807 1.0000
13.250 1.3363 0.05606 0.04770 -0.0324 0.0771 1.0000
13.500 1.3749 0.06042 0.05206 -0.0345 0.0707 1.0000
13.750 1.3583 0.06252 0.05452 -0.0310 0.0694 1.0000
14.000 1.3458 0.06527 0.05761 -0.0285 0.0677 1.0000
14.250 1.3357 0.06840 0.06104 -0.0266 0.0656 1.0000
14.500 1.3366 0.07150 0.06429 -0.0256 0.0629 1.0000
14.750 1.3588 0.07774 0.07054 -0.0266 0.0593 1.0000
15.000 1.3353 0.08125 0.07436 -0.0246 0.0590 1.0000
15.250 1.3113 0.08519 0.07860 -0.0233 0.0588 1.0000
15.500 1.2875 0.08980 0.08349 -0.0228 0.0586 1.0000
15.750 1.2620 0.09478 0.08875 -0.0228 0.0585 1.0000
16.000 1.2363 0.10029 0.09452 -0.0236 0.0584 1.0000
16.250 1.2114 0.10635 0.10080 -0.0251 0.0586 1.0000
16.500 1.1863 0.11287 0.10754 -0.0274 0.0587 1.0000
16.750 1.1627 0.11990 0.11474 -0.0302 0.0590 1.0000
17.000 1.1396 0.12757 0.12256 -0.0336 0.0593 1.0000
17.250 1.0147 0.15563 0.15108 -0.0537 0.0702 1.0000
17.500 1.0129 0.16282 0.15827 -0.0561 0.0711 1.0000
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