FX 83-W-108 (fx83w108-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 83-W-108 (fx83w108-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.38 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx83w108-il-1000000-n5.txt Download as CSV file: xf-fx83w108-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: FX 83-W-108
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.000 -0.8216 0.06056 0.05815 -0.0757 1.0000 0.0099
-13.750 -0.8744 0.05027 0.04774 -0.0811 1.0000 0.0099
-13.500 -0.8889 0.04108 0.03837 -0.0922 0.9971 0.0099
-13.250 -0.8893 0.03005 0.02699 -0.1116 0.9877 0.0099
-13.000 -0.8715 0.02720 0.02396 -0.1159 0.9816 0.0100
-12.750 -0.8505 0.02520 0.02181 -0.1186 0.9766 0.0101
-12.500 -0.8286 0.02364 0.02012 -0.1203 0.9701 0.0102
-12.250 -0.8037 0.02233 0.01868 -0.1220 0.9641 0.0104
-12.000 -0.7755 0.02097 0.01718 -0.1242 0.9582 0.0105
-11.750 -0.7435 0.01986 0.01595 -0.1267 0.9532 0.0107
-11.500 -0.7097 0.01871 0.01466 -0.1296 0.9471 0.0108
-11.250 -0.6712 0.01770 0.01351 -0.1332 0.9424 0.0111
-11.000 -0.6353 0.01677 0.01244 -0.1361 0.9347 0.0112
-10.750 -0.5990 0.01600 0.01154 -0.1389 0.9269 0.0115
-10.500 -0.5682 0.01529 0.01070 -0.1403 0.9161 0.0116
-10.250 -0.5392 0.01472 0.00998 -0.1413 0.9056 0.0118
-10.000 -0.5119 0.01425 0.00939 -0.1417 0.8957 0.0120
-9.750 -0.4877 0.01369 0.00872 -0.1415 0.8859 0.0122
-9.500 -0.4637 0.01310 0.00803 -0.1413 0.8773 0.0126
-9.250 -0.4393 0.01266 0.00751 -0.1410 0.8687 0.0130
-9.000 -0.4145 0.01230 0.00707 -0.1406 0.8611 0.0133
-8.750 -0.3897 0.01195 0.00664 -0.1403 0.8532 0.0136
-8.500 -0.3647 0.01163 0.00624 -0.1399 0.8465 0.0139
-8.250 -0.3394 0.01133 0.00587 -0.1396 0.8397 0.0143
-8.000 -0.3141 0.01103 0.00549 -0.1392 0.8338 0.0147
-7.750 -0.2885 0.01074 0.00513 -0.1389 0.8279 0.0150
-7.500 -0.2628 0.01050 0.00482 -0.1386 0.8218 0.0154
-7.250 -0.2373 0.01019 0.00445 -0.1382 0.8165 0.0161
-7.000 -0.2113 0.00994 0.00417 -0.1380 0.8111 0.0170
-6.750 -0.1853 0.00973 0.00391 -0.1377 0.8059 0.0178
-6.500 -0.1589 0.00954 0.00368 -0.1374 0.8011 0.0187
-6.250 -0.1323 0.00936 0.00345 -0.1372 0.7962 0.0195
-6.000 -0.1061 0.00914 0.00321 -0.1369 0.7913 0.0212
-5.750 -0.0795 0.00898 0.00302 -0.1367 0.7868 0.0228
-5.500 -0.0525 0.00884 0.00285 -0.1365 0.7822 0.0242
-5.250 -0.0259 0.00866 0.00265 -0.1363 0.7775 0.0259
-4.750 0.0278 0.00838 0.00233 -0.1358 0.7691 0.0297
-4.500 0.0548 0.00826 0.00217 -0.1356 0.7649 0.0315
-4.250 0.0816 0.00812 0.00203 -0.1354 0.7607 0.0349
-4.000 0.1085 0.00802 0.00191 -0.1352 0.7568 0.0379
-3.750 0.1357 0.00787 0.00179 -0.1350 0.7530 0.0438
-3.500 0.1628 0.00776 0.00167 -0.1349 0.7490 0.0501
-3.250 0.1898 0.00765 0.00157 -0.1346 0.7450 0.0575
-3.000 0.2166 0.00754 0.00147 -0.1344 0.7413 0.0692
-2.750 0.2437 0.00739 0.00138 -0.1343 0.7377 0.0865
-2.500 0.2705 0.00722 0.00129 -0.1340 0.7336 0.1127
-2.250 0.2968 0.00703 0.00121 -0.1338 0.7296 0.1513
-2.000 0.3232 0.00688 0.00115 -0.1335 0.7260 0.1879
-1.750 0.3501 0.00673 0.00111 -0.1333 0.7221 0.2210
-1.500 0.3768 0.00662 0.00108 -0.1330 0.7175 0.2530
-1.250 0.4030 0.00651 0.00106 -0.1327 0.7128 0.2901
-1.000 0.4300 0.00646 0.00106 -0.1325 0.7089 0.3147
-0.750 0.4572 0.00640 0.00107 -0.1323 0.7049 0.3398
-0.500 0.4842 0.00637 0.00108 -0.1321 0.7009 0.3599
-0.250 0.5111 0.00636 0.00109 -0.1318 0.6968 0.3768
0.000 0.5383 0.00635 0.00111 -0.1316 0.6931 0.3908
0.250 0.5655 0.00633 0.00113 -0.1314 0.6887 0.4021
0.500 0.5924 0.00635 0.00115 -0.1311 0.6835 0.4103
0.750 0.6191 0.00636 0.00117 -0.1308 0.6782 0.4213
1.000 0.6459 0.00636 0.00121 -0.1305 0.6712 0.4313
1.250 0.6717 0.00640 0.00123 -0.1300 0.6621 0.4414
1.500 0.6968 0.00645 0.00127 -0.1293 0.6490 0.4527
1.750 0.7219 0.00649 0.00132 -0.1286 0.6358 0.4662
2.000 0.7460 0.00658 0.00138 -0.1278 0.6177 0.4799
2.250 0.7681 0.00674 0.00145 -0.1265 0.5879 0.4938
2.500 0.7913 0.00687 0.00155 -0.1255 0.5638 0.5103
2.750 0.8134 0.00705 0.00167 -0.1242 0.5366 0.5308
3.000 0.8353 0.00724 0.00181 -0.1230 0.5097 0.5530
3.250 0.8515 0.00769 0.00206 -0.1207 0.4508 0.5818
3.500 0.8662 0.00820 0.00237 -0.1181 0.3849 0.6198
3.750 0.8824 0.00858 0.00266 -0.1159 0.3360 0.6704
4.000 0.8978 0.00893 0.00296 -0.1134 0.2899 0.7319
4.250 0.9117 0.00914 0.00325 -0.1105 0.2537 0.8216
4.500 0.9616 0.00957 0.00370 -0.1160 0.2009 1.0000
4.750 0.9813 0.01000 0.00398 -0.1145 0.1708 1.0000
5.000 1.0013 0.01041 0.00425 -0.1131 0.1452 1.0000
5.250 1.0221 0.01076 0.00452 -0.1118 0.1256 1.0000
5.500 1.0410 0.01122 0.00484 -0.1102 0.1012 1.0000
5.750 1.0614 0.01158 0.00512 -0.1088 0.0862 1.0000
6.000 1.0821 0.01192 0.00540 -0.1075 0.0759 1.0000
6.250 1.1014 0.01227 0.00570 -0.1059 0.0652 1.0000
6.500 1.1207 0.01261 0.00600 -0.1043 0.0575 1.0000
6.750 1.1404 0.01295 0.00630 -0.1028 0.0506 1.0000
7.000 1.1597 0.01332 0.00664 -0.1013 0.0447 1.0000
7.250 1.1800 0.01365 0.00696 -0.1000 0.0409 1.0000
7.500 1.1992 0.01404 0.00732 -0.0986 0.0363 1.0000
7.750 1.2192 0.01439 0.00768 -0.0973 0.0340 1.0000
8.000 1.2388 0.01478 0.00807 -0.0959 0.0317 1.0000
8.250 1.2577 0.01521 0.00849 -0.0945 0.0294 1.0000
8.500 1.2775 0.01561 0.00891 -0.0933 0.0278 1.0000
8.750 1.2970 0.01601 0.00934 -0.0920 0.0266 1.0000
9.000 1.3156 0.01648 0.00981 -0.0907 0.0247 1.0000
9.250 1.3334 0.01701 0.01034 -0.0893 0.0230 1.0000
9.500 1.3519 0.01749 0.01085 -0.0880 0.0219 1.0000
9.750 1.3702 0.01800 0.01139 -0.0867 0.0209 1.0000
10.000 1.3876 0.01856 0.01197 -0.0854 0.0196 1.0000
10.250 1.4043 0.01919 0.01261 -0.0839 0.0184 1.0000
10.500 1.4205 0.01986 0.01330 -0.0825 0.0176 1.0000
10.750 1.4374 0.02048 0.01397 -0.0812 0.0171 1.0000
11.000 1.4536 0.02117 0.01470 -0.0799 0.0164 1.0000
11.250 1.4689 0.02192 0.01549 -0.0785 0.0159 1.0000
11.500 1.4838 0.02271 0.01630 -0.0771 0.0153 1.0000
11.750 1.4981 0.02355 0.01719 -0.0757 0.0148 1.0000
12.000 1.5108 0.02452 0.01819 -0.0742 0.0141 1.0000
12.250 1.5236 0.02550 0.01921 -0.0727 0.0137 1.0000
12.500 1.5374 0.02641 0.02019 -0.0714 0.0135 1.0000
12.750 1.5514 0.02730 0.02113 -0.0702 0.0129 1.0000
13.000 1.5629 0.02841 0.02230 -0.0687 0.0128 1.0000
13.250 1.5753 0.02945 0.02338 -0.0675 0.0123 1.0000
13.500 1.5862 0.03063 0.02463 -0.0661 0.0120 1.0000
13.750 1.5962 0.03189 0.02594 -0.0647 0.0117 1.0000
14.000 1.6058 0.03320 0.02729 -0.0634 0.0113 1.0000
14.250 1.6137 0.03467 0.02883 -0.0620 0.0110 1.0000
14.500 1.6203 0.03630 0.03052 -0.0606 0.0107 1.0000
14.750 1.6273 0.03789 0.03219 -0.0593 0.0105 1.0000
15.000 1.6353 0.03943 0.03381 -0.0581 0.0104 1.0000
15.250 1.6419 0.04113 0.03558 -0.0570 0.0103 1.0000
15.500 1.6494 0.04279 0.03732 -0.0560 0.0101 1.0000
15.750 1.6556 0.04460 0.03922 -0.0550 0.0099 1.0000
16.000 1.6608 0.04653 0.04123 -0.0540 0.0097 1.0000
16.250 1.6648 0.04863 0.04342 -0.0531 0.0095 1.0000
16.500 1.6690 0.05077 0.04564 -0.0524 0.0094 1.0000
16.750 1.6721 0.05308 0.04804 -0.0517 0.0092 1.0000
17.000 1.6756 0.05538 0.05040 -0.0511 0.0089 1.0000
17.250 1.6762 0.05805 0.05316 -0.0506 0.0088 1.0000
17.500 1.6765 0.06083 0.05603 -0.0502 0.0086 1.0000
17.750 1.6757 0.06381 0.05908 -0.0499 0.0084 1.0000
18.000 1.6731 0.06709 0.06244 -0.0498 0.0081 1.0000
18.250 1.6685 0.07071 0.06617 -0.0499 0.0080 1.0000
18.500 1.6653 0.07419 0.06975 -0.0501 0.0079 1.0000
18.750 1.6605 0.07798 0.07366 -0.0505 0.0078 1.0000
19.000 1.6548 0.08198 0.07777 -0.0510 0.0077 1.0000
19.250 1.6488 0.08613 0.08203 -0.0518 0.0076 1.0000
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Polar data table (+)
Polar graphs
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