FX 83-W-160 (fx83w160-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 83-W-160 (fx83w160-il) Reynolds number: 50,000 Max Cl/Cd: 24.51 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx83w160-il-50000-n5.txt Download as CSV file: xf-fx83w160-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5100 0.10677 0.09930 -0.0578 1.0000 0.0848
-11.250 -0.5535 0.09649 0.08909 -0.0615 1.0000 0.0849
-11.000 -0.6009 0.08739 0.08000 -0.0645 1.0000 0.0846
-10.750 -0.6495 0.08005 0.07264 -0.0662 1.0000 0.0842
-10.500 -0.6909 0.07486 0.06742 -0.0661 1.0000 0.0836
-10.250 -0.7327 0.07040 0.06288 -0.0655 0.9991 0.0832
-10.000 -0.7612 0.06447 0.05660 -0.0693 0.9915 0.0837
-9.750 -0.7753 0.05919 0.05080 -0.0719 0.9848 0.0852
-9.500 -0.7571 0.05796 0.04964 -0.0722 0.9805 0.0878
-9.250 -0.7446 0.05541 0.04685 -0.0737 0.9759 0.0908
-9.000 -0.7388 0.05247 0.04353 -0.0741 0.9702 0.0940
-8.750 -0.7246 0.04977 0.04045 -0.0753 0.9658 0.0979
-8.500 -0.7067 0.04850 0.03917 -0.0752 0.9616 0.1017
-8.250 -0.6903 0.04662 0.03698 -0.0755 0.9569 0.1065
-8.000 -0.6679 0.04495 0.03508 -0.0765 0.9531 0.1119
-7.750 -0.6482 0.04382 0.03387 -0.0764 0.9490 0.1171
-7.500 -0.6297 0.04233 0.03201 -0.0763 0.9445 0.1239
-7.250 -0.6059 0.04145 0.03121 -0.0766 0.9409 0.1301
-7.000 -0.5784 0.04030 0.02976 -0.0777 0.9378 0.1389
-6.750 -0.5621 0.03954 0.02908 -0.0765 0.9330 0.1457
-6.500 -0.5402 0.03865 0.02800 -0.0764 0.9289 0.1551
-6.250 -0.5154 0.03795 0.02730 -0.0768 0.9255 0.1653
-6.000 -0.4874 0.03724 0.02657 -0.0777 0.9226 0.1779
-5.750 -0.4714 0.03659 0.02587 -0.0765 0.9176 0.1897
-5.500 -0.4493 0.03597 0.02523 -0.0764 0.9133 0.2048
-5.250 -0.4239 0.03538 0.02467 -0.0768 0.9099 0.2224
-5.000 -0.3957 0.03483 0.02423 -0.0778 0.9071 0.2437
-4.750 -0.3781 0.03435 0.02383 -0.0769 0.9025 0.2655
-4.500 -0.3570 0.03392 0.02353 -0.0765 0.8980 0.2935
-4.250 -0.3313 0.03364 0.02344 -0.0768 0.8943 0.3301
-4.000 -0.3029 0.03363 0.02364 -0.0772 0.8912 0.3724
-3.750 -0.2840 0.03383 0.02393 -0.0758 0.8867 0.4093
-3.500 -0.2652 0.03417 0.02433 -0.0742 0.8817 0.4418
-3.250 -0.2403 0.03461 0.02474 -0.0736 0.8777 0.4730
-3.000 -0.2112 0.03506 0.02507 -0.0738 0.8745 0.5017
-2.750 -0.1928 0.03550 0.02544 -0.0722 0.8697 0.5232
-2.500 -0.1743 0.03588 0.02575 -0.0707 0.8647 0.5432
-2.250 -0.1507 0.03629 0.02607 -0.0699 0.8609 0.5628
-2.000 -0.1235 0.03668 0.02639 -0.0697 0.8578 0.5819
-1.750 -0.1052 0.03704 0.02670 -0.0681 0.8533 0.5985
-1.500 -0.0888 0.03735 0.02696 -0.0662 0.8479 0.6141
-1.250 -0.0657 0.03766 0.02721 -0.0655 0.8439 0.6304
-1.000 -0.0382 0.03793 0.02741 -0.0655 0.8408 0.6463
-0.750 -0.0198 0.03820 0.02763 -0.0642 0.8360 0.6596
-0.500 -0.0034 0.03844 0.02785 -0.0625 0.8302 0.6706
-0.250 0.0233 0.03864 0.02797 -0.0627 0.8260 0.6828
0.000 0.0541 0.03883 0.02809 -0.0634 0.8228 0.6944
0.250 0.0670 0.03912 0.02836 -0.0614 0.8161 0.7038
0.500 0.0907 0.03937 0.02855 -0.0614 0.8110 0.7147
0.750 0.1190 0.03957 0.02872 -0.0617 0.8072 0.7238
1.000 0.1444 0.03989 0.02898 -0.0620 0.8027 0.7342
1.250 0.1581 0.04023 0.02935 -0.0602 0.7959 0.7426
1.500 0.1864 0.04050 0.02958 -0.0608 0.7914 0.7532
1.750 0.2180 0.04069 0.02978 -0.0616 0.7880 0.7632
2.000 0.2282 0.04117 0.03028 -0.0597 0.7795 0.7727
2.250 0.2559 0.04140 0.03052 -0.0600 0.7743 0.7827
2.500 0.2905 0.04154 0.03067 -0.0613 0.7707 0.7929
2.750 0.2995 0.04211 0.03128 -0.0593 0.7612 0.8032
3.000 0.3288 0.04230 0.03153 -0.0598 0.7562 0.8143
3.250 0.3502 0.04267 0.03196 -0.0593 0.7496 0.8266
3.500 0.3711 0.04302 0.03238 -0.0588 0.7418 0.8404
3.750 0.4059 0.04300 0.03246 -0.0599 0.7372 0.8567
4.000 0.4182 0.04351 0.03309 -0.0584 0.7267 0.8758
4.250 0.4562 0.04351 0.03322 -0.0602 0.7212 0.9032
4.500 0.4770 0.04390 0.03376 -0.0606 0.7103 1.0000
4.750 0.5164 0.04408 0.03393 -0.0630 0.7042 1.0000
5.000 0.5368 0.04475 0.03461 -0.0632 0.6929 1.0000
5.250 0.5773 0.04467 0.03456 -0.0652 0.6866 1.0000
5.500 0.5954 0.04533 0.03523 -0.0648 0.6740 1.0000
5.750 0.6400 0.04482 0.03476 -0.0667 0.6683 1.0000
6.000 0.6568 0.04533 0.03532 -0.0658 0.6541 1.0000
6.250 0.6784 0.04555 0.03559 -0.0651 0.6405 1.0000
6.500 0.7060 0.04535 0.03544 -0.0648 0.6279 1.0000
6.750 0.7451 0.04432 0.03450 -0.0652 0.6182 1.0000
7.000 0.7653 0.04434 0.03458 -0.0640 0.6027 1.0000
7.250 0.7865 0.04425 0.03459 -0.0628 0.5872 1.0000
7.500 0.8084 0.04407 0.03450 -0.0616 0.5715 1.0000
7.750 0.8313 0.04373 0.03425 -0.0604 0.5554 1.0000
8.000 0.8547 0.04332 0.03393 -0.0591 0.5380 1.0000
8.250 0.8781 0.04292 0.03363 -0.0578 0.5191 1.0000
8.500 0.9047 0.04225 0.03302 -0.0566 0.4987 1.0000
8.750 0.9252 0.04217 0.03300 -0.0551 0.4729 1.0000
9.000 0.9557 0.04126 0.03205 -0.0540 0.4448 1.0000
9.250 0.9828 0.04071 0.03134 -0.0526 0.4109 1.0000
9.500 1.0031 0.04092 0.03133 -0.0511 0.3756 1.0000
9.750 1.0184 0.04165 0.03180 -0.0494 0.3432 1.0000
10.000 1.0288 0.04292 0.03291 -0.0477 0.3149 1.0000
10.250 1.0396 0.04424 0.03402 -0.0462 0.2914 1.0000
10.500 1.0502 0.04569 0.03537 -0.0448 0.2710 1.0000
10.750 1.0611 0.04717 0.03678 -0.0435 0.2528 1.0000
11.000 1.0730 0.04863 0.03815 -0.0424 0.2371 1.0000
11.250 1.0853 0.05008 0.03952 -0.0413 0.2229 1.0000
11.500 1.0978 0.05157 0.04097 -0.0403 0.2096 1.0000
11.750 1.1104 0.05312 0.04259 -0.0394 0.1972 1.0000
12.000 1.1239 0.05462 0.04410 -0.0385 0.1864 1.0000
12.250 1.1391 0.05599 0.04540 -0.0377 0.1766 1.0000
12.500 1.1515 0.05772 0.04729 -0.0370 0.1671 1.0000
12.750 1.1686 0.05906 0.04858 -0.0363 0.1588 1.0000
13.000 1.1796 0.06095 0.05068 -0.0356 0.1508 1.0000
13.250 1.1968 0.06235 0.05202 -0.0350 0.1439 1.0000
13.500 1.2039 0.06466 0.05459 -0.0342 0.1372 1.0000
13.750 1.2187 0.06618 0.05605 -0.0336 0.1311 1.0000
14.000 1.2231 0.06886 0.05902 -0.0329 0.1257 1.0000
14.250 1.2278 0.07134 0.06166 -0.0322 0.1207 1.0000
14.500 1.2421 0.07296 0.06319 -0.0317 0.1159 1.0000
14.750 1.2349 0.07678 0.06740 -0.0312 0.1121 1.0000
15.000 1.2324 0.08013 0.07098 -0.0309 0.1083 1.0000
15.250 1.2394 0.08235 0.07320 -0.0306 0.1046 1.0000
15.500 1.2362 0.08599 0.07704 -0.0305 0.1017 1.0000
15.750 1.2178 0.09152 0.08292 -0.0312 0.0995 1.0000
16.000 1.1992 0.09735 0.08905 -0.0324 0.0974 1.0000
16.250 1.1816 0.10326 0.09520 -0.0341 0.0955 1.0000
16.500 1.1705 0.10844 0.10052 -0.0358 0.0934 1.0000
16.750 1.1813 0.11025 0.10227 -0.0358 0.0907 1.0000
17.000 1.1361 0.12166 0.11402 -0.0415 0.0904 1.0000
17.250 1.0632 0.14103 0.13367 -0.0531 0.0905 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 83-W-160 (fx83w160-il)