FX 83-W-160 (fx83w160-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: FX 83-W-160 (fx83w160-il) Reynolds number: 200,000 Max Cl/Cd: 69.58 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx83w160-il-200000-n5.txt Download as CSV file: xf-fx83w160-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.6953 0.09438 0.08976 -0.0797 1.0000 0.0306
-15.750 -0.7310 0.08543 0.08063 -0.0839 1.0000 0.0306
-15.500 -0.7575 0.07874 0.07379 -0.0866 1.0000 0.0308
-15.250 -0.7781 0.07359 0.06851 -0.0880 1.0000 0.0309
-15.000 -0.7982 0.06897 0.06376 -0.0890 1.0000 0.0312
-14.750 -0.8048 0.06360 0.05818 -0.0935 0.9983 0.0317
-14.500 -0.8066 0.05871 0.05305 -0.0982 0.9955 0.0323
-14.250 -0.8021 0.05516 0.04940 -0.1015 0.9925 0.0328
-14.000 -0.7944 0.05218 0.04636 -0.1046 0.9894 0.0333
-13.750 -0.7852 0.04925 0.04334 -0.1078 0.9866 0.0340
-13.500 -0.7774 0.04653 0.04052 -0.1104 0.9824 0.0347
-13.250 -0.7672 0.04389 0.03776 -0.1132 0.9785 0.0356
-13.000 -0.7544 0.04143 0.03514 -0.1159 0.9753 0.0364
-12.750 -0.7458 0.03928 0.03281 -0.1173 0.9694 0.0374
-12.500 -0.7305 0.03721 0.03070 -0.1198 0.9660 0.0383
-12.250 -0.7194 0.03543 0.02886 -0.1211 0.9603 0.0392
-12.000 -0.7040 0.03369 0.02704 -0.1229 0.9554 0.0405
-11.750 -0.6838 0.03197 0.02519 -0.1253 0.9525 0.0419
-11.500 -0.6747 0.03061 0.02371 -0.1251 0.9451 0.0430
-11.250 -0.6583 0.02907 0.02213 -0.1265 0.9407 0.0442
-11.000 -0.6367 0.02768 0.02067 -0.1287 0.9378 0.0460
-10.750 -0.6326 0.02677 0.01967 -0.1268 0.9285 0.0475
-10.500 -0.6080 0.02570 0.01846 -0.1281 0.9252 0.0496
-10.250 -0.5810 0.02457 0.01731 -0.1301 0.9230 0.0518
-10.000 -0.5726 0.02396 0.01664 -0.1278 0.9151 0.0537
-9.750 -0.5481 0.02320 0.01577 -0.1285 0.9115 0.0565
-9.500 -0.5208 0.02234 0.01489 -0.1299 0.9090 0.0594
-9.250 -0.4904 0.02162 0.01409 -0.1315 0.9070 0.0632
-9.000 -0.4795 0.02118 0.01358 -0.1291 0.8995 0.0659
-8.750 -0.4551 0.02052 0.01292 -0.1295 0.8956 0.0698
-8.500 -0.4254 0.01996 0.01225 -0.1306 0.8930 0.0746
-8.250 -0.3954 0.01929 0.01159 -0.1320 0.8909 0.0798
-8.000 -0.3789 0.01897 0.01121 -0.1303 0.8851 0.0844
-7.750 -0.3568 0.01849 0.01074 -0.1299 0.8804 0.0899
-7.250 -0.2970 0.01752 0.00971 -0.1319 0.8749 0.1041
-7.000 -0.2685 0.01712 0.00926 -0.1325 0.8721 0.1117
-6.750 -0.2531 0.01686 0.00901 -0.1306 0.8659 0.1184
-6.500 -0.2262 0.01649 0.00861 -0.1308 0.8622 0.1266
-6.250 -0.1960 0.01610 0.00820 -0.1317 0.8594 0.1371
-6.000 -0.1644 0.01567 0.00777 -0.1329 0.8571 0.1488
-5.750 -0.1436 0.01542 0.00754 -0.1319 0.8526 0.1602
-5.500 -0.1216 0.01516 0.00731 -0.1311 0.8480 0.1742
-5.250 -0.0944 0.01480 0.00700 -0.1314 0.8447 0.1939
-5.000 -0.0642 0.01442 0.00668 -0.1323 0.8420 0.2194
-4.750 -0.0325 0.01401 0.00636 -0.1335 0.8397 0.2492
-4.500 -0.0136 0.01380 0.00626 -0.1320 0.8347 0.2787
-4.250 0.0099 0.01357 0.00614 -0.1315 0.8305 0.3113
-4.000 0.0379 0.01335 0.00599 -0.1317 0.8274 0.3449
-3.750 0.0681 0.01313 0.00588 -0.1324 0.8248 0.3797
-3.500 0.1003 0.01298 0.00578 -0.1333 0.8226 0.4130
-3.250 0.1209 0.01300 0.00589 -0.1319 0.8178 0.4379
-3.000 0.1452 0.01303 0.00593 -0.1312 0.8135 0.4595
-2.750 0.1741 0.01302 0.00592 -0.1314 0.8102 0.4768
-2.500 0.2054 0.01301 0.00589 -0.1320 0.8075 0.4913
-2.250 0.2387 0.01300 0.00584 -0.1331 0.8052 0.5045
-2.000 0.2588 0.01313 0.00593 -0.1315 0.8003 0.5164
-1.750 0.2832 0.01321 0.00603 -0.1308 0.7962 0.5269
-1.500 0.3118 0.01325 0.00604 -0.1309 0.7930 0.5380
-1.250 0.3425 0.01329 0.00606 -0.1314 0.7905 0.5494
-1.000 0.3746 0.01330 0.00607 -0.1322 0.7883 0.5583
-0.750 0.3962 0.01343 0.00621 -0.1310 0.7842 0.5664
-0.500 0.4189 0.01352 0.00630 -0.1300 0.7798 0.5731
-0.250 0.4466 0.01354 0.00634 -0.1299 0.7763 0.5785
0.000 0.4772 0.01355 0.00632 -0.1304 0.7735 0.5848
0.250 0.5096 0.01355 0.00629 -0.1314 0.7714 0.5909
0.500 0.5309 0.01366 0.00646 -0.1301 0.7671 0.5959
0.750 0.5528 0.01374 0.00656 -0.1289 0.7621 0.6010
1.000 0.5819 0.01374 0.00653 -0.1291 0.7581 0.6061
1.250 0.6137 0.01371 0.00652 -0.1298 0.7552 0.6105
1.500 0.6419 0.01375 0.00660 -0.1299 0.7521 0.6151
1.750 0.6593 0.01391 0.00681 -0.1279 0.7466 0.6204
2.000 0.6860 0.01394 0.00684 -0.1276 0.7419 0.6260
2.250 0.7181 0.01387 0.00681 -0.1283 0.7380 0.6307
2.500 0.7394 0.01393 0.00693 -0.1270 0.7318 0.6355
2.750 0.7622 0.01395 0.00697 -0.1259 0.7249 0.6401
3.000 0.7966 0.01380 0.00679 -0.1270 0.7186 0.6445
3.250 0.8096 0.01379 0.00686 -0.1238 0.7067 0.6485
3.500 0.8301 0.01372 0.00680 -0.1221 0.6947 0.6534
3.750 0.8570 0.01363 0.00669 -0.1216 0.6839 0.6587
4.000 0.8730 0.01369 0.00680 -0.1192 0.6735 0.6635
4.250 0.8943 0.01370 0.00685 -0.1177 0.6638 0.6684
4.500 0.9144 0.01374 0.00693 -0.1161 0.6537 0.6741
4.750 0.9312 0.01385 0.00709 -0.1138 0.6430 0.6802
5.000 0.9510 0.01391 0.00720 -0.1121 0.6311 0.6857
5.250 0.9689 0.01402 0.00732 -0.1100 0.6158 0.6918
5.750 0.9991 0.01436 0.00766 -0.1049 0.5747 0.7046
6.000 1.0130 0.01461 0.00783 -0.1021 0.5465 0.7126
6.250 1.0233 0.01497 0.00810 -0.0988 0.5137 0.7209
6.500 1.0287 0.01553 0.00849 -0.0947 0.4744 0.7309
6.750 1.0310 0.01625 0.00904 -0.0903 0.4342 0.7418
7.000 1.0320 0.01712 0.00974 -0.0859 0.3968 0.7547
7.500 1.0387 0.01892 0.01133 -0.0784 0.3297 0.7910
7.750 1.0435 0.01984 0.01220 -0.0751 0.2986 0.8221
8.000 1.0550 0.02075 0.01315 -0.0735 0.2673 0.9159
8.500 1.0674 0.02276 0.01489 -0.0681 0.2209 1.0000
8.750 1.0779 0.02376 0.01580 -0.0662 0.2037 1.0000
9.000 1.0888 0.02475 0.01672 -0.0643 0.1889 1.0000
9.250 1.1001 0.02576 0.01766 -0.0626 0.1766 1.0000
9.500 1.1129 0.02669 0.01857 -0.0611 0.1655 1.0000
9.750 1.1252 0.02767 0.01953 -0.0596 0.1566 1.0000
10.000 1.1374 0.02868 0.02052 -0.0581 0.1480 1.0000
10.250 1.1502 0.02967 0.02151 -0.0567 0.1402 1.0000
10.500 1.1620 0.03075 0.02257 -0.0553 0.1325 1.0000
10.750 1.1747 0.03178 0.02362 -0.0540 0.1256 1.0000
11.000 1.1863 0.03291 0.02474 -0.0527 0.1189 1.0000
11.250 1.1983 0.03402 0.02587 -0.0515 0.1126 1.0000
11.500 1.2101 0.03519 0.02704 -0.0502 0.1063 1.0000
11.750 1.2211 0.03643 0.02829 -0.0490 0.1010 1.0000
12.000 1.2334 0.03759 0.02949 -0.0479 0.0956 1.0000
12.250 1.2425 0.03901 0.03090 -0.0467 0.0909 1.0000
12.500 1.2552 0.04019 0.03215 -0.0457 0.0865 1.0000
12.750 1.2650 0.04161 0.03359 -0.0447 0.0821 1.0000
13.000 1.2744 0.04310 0.03510 -0.0436 0.0787 1.0000
13.250 1.2853 0.04449 0.03658 -0.0427 0.0749 1.0000
13.500 1.2937 0.04611 0.03822 -0.0417 0.0717 1.0000
13.750 1.3016 0.04780 0.03995 -0.0408 0.0688 1.0000
14.000 1.3112 0.04938 0.04162 -0.0399 0.0657 1.0000
14.250 1.3189 0.05117 0.04345 -0.0391 0.0629 1.0000
14.500 1.3243 0.05321 0.04552 -0.0383 0.0607 1.0000
14.750 1.3333 0.05494 0.04737 -0.0377 0.0581 1.0000
15.000 1.3401 0.05691 0.04941 -0.0371 0.0557 1.0000
15.250 1.3449 0.05912 0.05167 -0.0365 0.0538 1.0000
15.500 1.3497 0.06139 0.05400 -0.0360 0.0520 1.0000
15.750 1.3555 0.06358 0.05632 -0.0356 0.0501 1.0000
16.000 1.3601 0.06596 0.05878 -0.0353 0.0482 1.0000
16.250 1.3620 0.06868 0.06155 -0.0351 0.0467 1.0000
16.500 1.3636 0.07149 0.06442 -0.0350 0.0454 1.0000
16.750 1.3673 0.07411 0.06718 -0.0350 0.0440 1.0000
17.000 1.3693 0.07699 0.07017 -0.0351 0.0425 1.0000
17.250 1.3701 0.08009 0.07337 -0.0354 0.0413 1.0000
17.500 1.3690 0.08349 0.07683 -0.0358 0.0402 1.0000
17.750 1.3678 0.08695 0.08038 -0.0364 0.0392 1.0000
18.000 1.3681 0.09029 0.08387 -0.0370 0.0381 1.0000
18.250 1.3670 0.09387 0.08758 -0.0378 0.0370 1.0000
18.500 1.3650 0.09765 0.09147 -0.0389 0.0361 1.0000
18.750 1.3622 0.10162 0.09554 -0.0402 0.0353 1.0000
19.000 1.3579 0.10586 0.09985 -0.0417 0.0345 1.0000
19.250 1.3543 0.11003 0.10413 -0.0432 0.0338 1.0000
|
Polar data table (+)
Polar graphs
<< Back to FX 83-W-160 (fx83w160-il)