FX 83-W-160 (fx83w160-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 83-W-160 (fx83w160-il) Reynolds number: 100,000 Max Cl/Cd: 42.76 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx83w160-il-100000-n5.txt Download as CSV file: xf-fx83w160-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 83-W-160
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 -0.6023 0.09266 0.08703 -0.0727 1.0000 0.0492
-13.250 -0.6767 0.07882 0.07300 -0.0793 1.0000 0.0486
-13.000 -0.7202 0.07105 0.06505 -0.0827 0.9993 0.0485
-12.750 -0.7430 0.06313 0.05679 -0.0900 0.9947 0.0487
-12.500 -0.7580 0.05723 0.05055 -0.0951 0.9890 0.0492
-12.250 -0.7599 0.05334 0.04643 -0.0987 0.9839 0.0501
-12.000 -0.7492 0.05129 0.04436 -0.1007 0.9788 0.0512
-11.750 -0.7433 0.04890 0.04185 -0.1029 0.9733 0.0525
-11.500 -0.7401 0.04645 0.03921 -0.1045 0.9669 0.0536
-11.250 -0.7413 0.04430 0.03684 -0.1046 0.9594 0.0549
-11.000 -0.7340 0.04197 0.03415 -0.1056 0.9537 0.0566
-10.750 -0.7220 0.04050 0.03261 -0.1054 0.9481 0.0580
-10.500 -0.7075 0.03927 0.03135 -0.1054 0.9424 0.0597
-10.250 -0.6864 0.03778 0.02969 -0.1066 0.9388 0.0623
-10.000 -0.6778 0.03649 0.02814 -0.1052 0.9322 0.0648
-9.750 -0.6603 0.03540 0.02705 -0.1050 0.9276 0.0670
-9.500 -0.6365 0.03430 0.02588 -0.1059 0.9244 0.0700
-9.250 -0.6174 0.03327 0.02465 -0.1057 0.9201 0.0735
-9.000 -0.6044 0.03244 0.02378 -0.1043 0.9138 0.0764
-8.750 -0.5807 0.03157 0.02287 -0.1048 0.9102 0.0805
-8.500 -0.5535 0.03064 0.02177 -0.1058 0.9078 0.0856
-8.250 -0.5396 0.03003 0.02119 -0.1043 0.9023 0.0893
-8.000 -0.5209 0.02940 0.02046 -0.1035 0.8971 0.0945
-7.750 -0.4952 0.02863 0.01966 -0.1040 0.8939 0.1002
-7.500 -0.4659 0.02793 0.01887 -0.1051 0.8916 0.1076
-7.250 -0.4462 0.02737 0.01831 -0.1044 0.8875 0.1136
-7.000 -0.4316 0.02698 0.01787 -0.1027 0.8813 0.1199
-6.750 -0.4058 0.02637 0.01725 -0.1030 0.8780 0.1280
-6.500 -0.3759 0.02582 0.01661 -0.1039 0.8756 0.1379
-6.250 -0.3451 0.02518 0.01601 -0.1052 0.8738 0.1488
-6.000 -0.3368 0.02505 0.01588 -0.1022 0.8668 0.1571
-5.750 -0.3131 0.02468 0.01547 -0.1020 0.8628 0.1700
-5.500 -0.2846 0.02416 0.01499 -0.1027 0.8601 0.1862
-5.250 -0.2536 0.02359 0.01450 -0.1039 0.8581 0.2063
-5.000 -0.2212 0.02302 0.01402 -0.1053 0.8565 0.2318
-4.750 -0.2164 0.02311 0.01419 -0.1018 0.8484 0.2506
-4.500 -0.1907 0.02276 0.01395 -0.1020 0.8451 0.2835
-4.250 -0.1610 0.02238 0.01371 -0.1027 0.8427 0.3243
-4.000 -0.1292 0.02207 0.01355 -0.1036 0.8408 0.3666
-3.750 -0.0961 0.02189 0.01348 -0.1046 0.8394 0.4081
-3.500 -0.0926 0.02241 0.01405 -0.1006 0.8304 0.4306
-3.250 -0.0648 0.02249 0.01415 -0.1005 0.8273 0.4587
-3.000 -0.0335 0.02252 0.01412 -0.1011 0.8250 0.4829
-2.750 -0.0008 0.02255 0.01412 -0.1018 0.8233 0.5020
-2.500 0.0118 0.02304 0.01453 -0.0994 0.8167 0.5170
-2.250 0.0337 0.02330 0.01477 -0.0984 0.8120 0.5305
-2.000 0.0623 0.02341 0.01485 -0.0984 0.8093 0.5443
-1.750 0.0930 0.02347 0.01486 -0.0988 0.8074 0.5580
-1.500 0.1254 0.02348 0.01482 -0.0995 0.8058 0.5722
-1.250 0.1298 0.02426 0.01563 -0.0957 0.7975 0.5811
-1.000 0.1550 0.02441 0.01576 -0.0952 0.7937 0.5927
-0.750 0.1847 0.02444 0.01577 -0.0955 0.7913 0.6037
-0.500 0.2159 0.02441 0.01572 -0.0959 0.7895 0.6123
-0.250 0.2490 0.02432 0.01560 -0.0968 0.7882 0.6207
0.250 0.2776 0.02525 0.01655 -0.0927 0.7751 0.6343
0.500 0.3111 0.02511 0.01636 -0.0937 0.7730 0.6428
0.750 0.3455 0.02487 0.01614 -0.0946 0.7714 0.6486
1.250 0.3753 0.02591 0.01717 -0.0911 0.7582 0.6616
1.500 0.4063 0.02578 0.01710 -0.0914 0.7561 0.6674
1.750 0.4404 0.02558 0.01692 -0.0923 0.7544 0.6748
2.250 0.4705 0.02655 0.01797 -0.0887 0.7407 0.6874
2.500 0.5057 0.02623 0.01767 -0.0896 0.7385 0.6942
2.750 0.5429 0.02585 0.01733 -0.0909 0.7369 0.7003
3.250 0.5753 0.02669 0.01827 -0.0875 0.7223 0.7132
3.500 0.6141 0.02614 0.01778 -0.0889 0.7203 0.7199
4.000 0.6536 0.02658 0.01834 -0.0864 0.7054 0.7347
4.250 0.6950 0.02578 0.01763 -0.0878 0.7031 0.7423
4.750 0.7491 0.02505 0.01706 -0.0865 0.6866 0.7599
5.000 0.7615 0.02526 0.01734 -0.0839 0.6736 0.7699
5.250 0.8106 0.02383 0.01599 -0.0861 0.6684 0.7798
5.500 0.8168 0.02434 0.01662 -0.0826 0.6546 0.7925
5.750 0.8324 0.02448 0.01688 -0.0805 0.6424 0.8078
6.000 0.8699 0.02357 0.01608 -0.0811 0.6339 0.8267
6.250 0.8815 0.02383 0.01651 -0.0784 0.6190 0.8549
6.500 0.9007 0.02375 0.01664 -0.0771 0.6033 0.9535
6.750 0.9200 0.02389 0.01679 -0.0758 0.5869 1.0000
7.000 0.9449 0.02382 0.01670 -0.0752 0.5675 1.0000
7.250 0.9655 0.02396 0.01681 -0.0740 0.5429 1.0000
7.500 0.9902 0.02389 0.01663 -0.0732 0.5107 1.0000
7.750 1.0169 0.02378 0.01626 -0.0724 0.4693 1.0000
8.000 1.0338 0.02425 0.01647 -0.0707 0.4244 1.0000
8.250 1.0441 0.02514 0.01706 -0.0683 0.3823 1.0000
8.500 1.0513 0.02625 0.01792 -0.0658 0.3458 1.0000
8.750 1.0583 0.02745 0.01892 -0.0634 0.3131 1.0000
9.000 1.0654 0.02869 0.02000 -0.0611 0.2849 1.0000
9.250 1.0730 0.02996 0.02111 -0.0590 0.2608 1.0000
9.500 1.0816 0.03121 0.02224 -0.0571 0.2398 1.0000
9.750 1.0908 0.03246 0.02339 -0.0554 0.2214 1.0000
10.000 1.1005 0.03372 0.02456 -0.0537 0.2060 1.0000
10.500 1.1222 0.03616 0.02693 -0.0509 0.1804 1.0000
10.750 1.1334 0.03740 0.02815 -0.0495 0.1700 1.0000
11.000 1.1434 0.03874 0.02944 -0.0482 0.1613 1.0000
11.250 1.1559 0.03995 0.03070 -0.0470 0.1523 1.0000
11.500 1.1651 0.04139 0.03208 -0.0457 0.1452 1.0000
11.750 1.1781 0.04260 0.03339 -0.0447 0.1376 1.0000
12.000 1.1872 0.04410 0.03485 -0.0435 0.1312 1.0000
12.250 1.1991 0.04544 0.03629 -0.0425 0.1245 1.0000
12.500 1.2086 0.04696 0.03783 -0.0414 0.1188 1.0000
12.750 1.2184 0.04850 0.03940 -0.0404 0.1131 1.0000
13.000 1.2282 0.05006 0.04105 -0.0395 0.1076 1.0000
13.500 1.2456 0.05346 0.04456 -0.0377 0.0980 1.0000
13.750 1.2533 0.05527 0.04643 -0.0369 0.0938 1.0000
14.000 1.2601 0.05720 0.04836 -0.0361 0.0901 1.0000
14.250 1.2685 0.05906 0.05038 -0.0354 0.0859 1.0000
14.500 1.2748 0.06111 0.05250 -0.0348 0.0826 1.0000
14.750 1.2800 0.06327 0.05463 -0.0342 0.0798 1.0000
15.000 1.2868 0.06542 0.05701 -0.0336 0.0764 1.0000
15.250 1.2920 0.06771 0.05940 -0.0332 0.0736 1.0000
15.500 1.2957 0.07013 0.06187 -0.0329 0.0712 1.0000
15.750 1.3002 0.07258 0.06438 -0.0326 0.0690 1.0000
16.000 1.3034 0.07530 0.06731 -0.0324 0.0665 1.0000
16.250 1.3054 0.07812 0.07026 -0.0323 0.0643 1.0000
16.500 1.3068 0.08098 0.07320 -0.0324 0.0624 1.0000
16.750 1.3097 0.08370 0.07592 -0.0325 0.0608 1.0000
17.000 1.3077 0.08732 0.07982 -0.0329 0.0590 1.0000
17.250 1.3055 0.09096 0.08366 -0.0335 0.0573 1.0000
17.500 1.3030 0.09464 0.08748 -0.0343 0.0557 1.0000
17.750 1.3016 0.09816 0.09110 -0.0351 0.0544 1.0000
18.000 1.3022 0.10136 0.09431 -0.0360 0.0532 1.0000
18.250 1.2939 0.10620 0.09938 -0.0376 0.0520 1.0000
18.500 1.2827 0.11169 0.10514 -0.0398 0.0509 1.0000
18.750 1.2711 0.11737 0.11105 -0.0423 0.0499 1.0000
19.000 1.2584 0.12339 0.11728 -0.0453 0.0490 1.0000
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Polar data table (+)
Polar graphs
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