FX 83-W-108 (fx83w108-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 83-W-108 (fx83w108-il) Reynolds number: 200,000 Max Cl/Cd: 90.49 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx83w108-il-200000.txt Download as CSV file: xf-fx83w108-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3746 0.11248 0.10889 -0.0481 1.0000 0.0577
-10.000 -0.3874 0.11020 0.10669 -0.0477 1.0000 0.0579
-9.750 -0.4018 0.10852 0.10509 -0.0458 1.0000 0.0579
-9.500 -0.4190 0.10704 0.10369 -0.0433 1.0000 0.0580
-9.250 -0.4113 0.10302 0.09969 -0.0389 1.0000 0.0593
-9.000 -0.4023 0.10150 0.09817 -0.0368 0.9993 0.0606
-8.750 -0.3820 0.09834 0.09500 -0.0397 0.9967 0.0631
-8.500 -0.3682 0.09403 0.09069 -0.0449 0.9927 0.0662
-8.250 -0.3776 0.08572 0.08241 -0.0644 0.9811 0.0702
-8.000 -0.3699 0.07914 0.07585 -0.0682 0.9760 0.0715
-7.750 -0.3488 0.07710 0.07379 -0.0672 0.9726 0.0727
-7.500 -0.3252 0.07424 0.07091 -0.0697 0.9695 0.0748
-7.250 -0.3105 0.06996 0.06662 -0.0753 0.9616 0.0775
-7.000 -0.3254 0.03685 0.03157 -0.1131 0.9438 0.0473
-6.750 -0.2947 0.03217 0.02652 -0.1165 0.9419 0.0461
-6.500 -0.2778 0.02999 0.02395 -0.1158 0.9339 0.0465
-6.250 -0.2474 0.02694 0.02038 -0.1179 0.9308 0.0476
-6.000 -0.2135 0.02423 0.01742 -0.1202 0.9290 0.0491
-5.750 -0.1762 0.02255 0.01554 -0.1225 0.9276 0.0510
-5.500 -0.1569 0.02166 0.01450 -0.1211 0.9204 0.0528
-5.250 -0.1234 0.02067 0.01331 -0.1223 0.9174 0.0561
-5.000 -0.0875 0.01924 0.01175 -0.1242 0.9154 0.0605
-4.750 -0.0491 0.01827 0.01076 -0.1264 0.9138 0.0656
-4.500 -0.0111 0.01733 0.00974 -0.1285 0.9123 0.0725
-4.250 0.0053 0.01695 0.00940 -0.1265 0.9045 0.0778
-4.000 0.0382 0.01622 0.00866 -0.1276 0.9014 0.0877
-3.750 0.0735 0.01550 0.00797 -0.1292 0.8991 0.1033
-3.500 0.1095 0.01463 0.00731 -0.1311 0.8971 0.1461
-3.250 0.1244 0.01413 0.00731 -0.1290 0.8896 0.2582
-3.000 0.1555 0.01394 0.00728 -0.1297 0.8859 0.3337
-2.750 0.1905 0.01385 0.00718 -0.1310 0.8833 0.3769
-2.500 0.2265 0.01376 0.00707 -0.1325 0.8812 0.4090
-2.250 0.2421 0.01397 0.00732 -0.1301 0.8734 0.4290
-2.000 0.2733 0.01393 0.00724 -0.1307 0.8698 0.4540
-1.750 0.3071 0.01379 0.00715 -0.1317 0.8672 0.4779
-1.500 0.3310 0.01390 0.00727 -0.1308 0.8621 0.5014
-1.250 0.3551 0.01391 0.00735 -0.1300 0.8566 0.5215
-1.000 0.3865 0.01378 0.00725 -0.1306 0.8533 0.5421
-0.750 0.4206 0.01363 0.00711 -0.1316 0.8507 0.5634
-0.500 0.4381 0.01380 0.00735 -0.1297 0.8436 0.5816
-0.250 0.4662 0.01369 0.00734 -0.1296 0.8393 0.6040
0.000 0.4986 0.01349 0.00723 -0.1302 0.8362 0.6323
0.250 0.5200 0.01352 0.00740 -0.1289 0.8304 0.6644
0.500 0.5434 0.01343 0.00751 -0.1278 0.8250 0.7114
0.750 0.5720 0.01309 0.00746 -0.1274 0.8216 0.7967
1.000 0.6319 0.01266 0.00725 -0.1338 0.8199 1.0000
1.250 0.6518 0.01299 0.00753 -0.1324 0.8128 1.0000
1.500 0.6807 0.01307 0.00756 -0.1326 0.8080 1.0000
1.750 0.7144 0.01306 0.00749 -0.1336 0.8046 1.0000
2.000 0.7346 0.01334 0.00778 -0.1321 0.7971 1.0000
2.250 0.7642 0.01337 0.00778 -0.1323 0.7919 1.0000
2.500 0.7986 0.01329 0.00766 -0.1332 0.7878 1.0000
2.750 0.8183 0.01345 0.00786 -0.1315 0.7784 1.0000
3.000 0.8542 0.01319 0.00755 -0.1324 0.7724 1.0000
3.250 0.8763 0.01319 0.00757 -0.1310 0.7616 1.0000
3.500 0.9036 0.01300 0.00739 -0.1302 0.7508 1.0000
3.750 0.9343 0.01271 0.00705 -0.1301 0.7399 1.0000
4.000 0.9600 0.01258 0.00692 -0.1291 0.7282 1.0000
4.250 0.9832 0.01255 0.00694 -0.1278 0.7164 1.0000
4.500 1.0081 0.01248 0.00689 -0.1268 0.7040 1.0000
4.750 1.0325 0.01239 0.00682 -0.1256 0.6901 1.0000
5.000 1.0551 0.01232 0.00677 -0.1241 0.6737 1.0000
5.250 1.0770 0.01229 0.00677 -0.1225 0.6550 1.0000
5.500 1.0985 0.01228 0.00673 -0.1207 0.6325 1.0000
5.750 1.1177 0.01236 0.00679 -0.1186 0.6052 1.0000
6.000 1.1347 0.01254 0.00689 -0.1161 0.5684 1.0000
6.250 1.1480 0.01292 0.00706 -0.1129 0.5157 1.0000
6.500 1.1539 0.01366 0.00741 -0.1085 0.4451 1.0000
6.750 1.1522 0.01477 0.00804 -0.1031 0.3648 1.0000
7.000 1.1469 0.01602 0.00884 -0.0972 0.2925 1.0000
7.250 1.1433 0.01736 0.00977 -0.0919 0.2281 1.0000
7.500 1.1424 0.01875 0.01079 -0.0874 0.1767 1.0000
7.750 1.1460 0.02002 0.01183 -0.0838 0.1413 1.0000
8.000 1.1499 0.02136 0.01298 -0.0804 0.1193 1.0000
8.250 1.1574 0.02255 0.01409 -0.0775 0.1035 1.0000
8.500 1.1643 0.02384 0.01530 -0.0748 0.0920 1.0000
8.750 1.1766 0.02484 0.01635 -0.0727 0.0837 1.0000
9.000 1.1843 0.02623 0.01769 -0.0703 0.0770 1.0000
9.250 1.1975 0.02724 0.01877 -0.0685 0.0716 1.0000
9.500 1.2067 0.02873 0.02020 -0.0663 0.0668 1.0000
9.750 1.2209 0.02987 0.02143 -0.0647 0.0631 1.0000
10.000 1.2346 0.03098 0.02259 -0.0631 0.0592 1.0000
10.250 1.2486 0.03250 0.02404 -0.0617 0.0555 1.0000
10.500 1.2677 0.03386 0.02550 -0.0606 0.0531 1.0000
10.750 1.2854 0.03509 0.02686 -0.0594 0.0509 1.0000
11.000 1.3030 0.03640 0.02825 -0.0582 0.0486 1.0000
11.250 1.3210 0.03778 0.02965 -0.0573 0.0466 1.0000
11.500 1.3521 0.04018 0.03211 -0.0578 0.0441 1.0000
11.750 1.3659 0.04172 0.03387 -0.0563 0.0431 1.0000
12.000 1.3803 0.04355 0.03595 -0.0549 0.0420 1.0000
12.250 1.3938 0.04562 0.03824 -0.0535 0.0411 1.0000
12.500 1.4045 0.04792 0.04077 -0.0520 0.0402 1.0000
12.750 1.4121 0.05018 0.04323 -0.0503 0.0394 1.0000
13.000 1.4174 0.05237 0.04559 -0.0486 0.0386 1.0000
13.250 1.4199 0.05475 0.04814 -0.0468 0.0379 1.0000
13.500 1.4239 0.05713 0.05061 -0.0454 0.0370 1.0000
13.750 1.4245 0.06085 0.05452 -0.0440 0.0364 1.0000
14.000 1.4150 0.06534 0.05931 -0.0422 0.0361 1.0000
14.250 1.3999 0.06993 0.06418 -0.0405 0.0359 1.0000
14.500 1.3834 0.07426 0.06877 -0.0391 0.0359 1.0000
14.750 1.3633 0.07911 0.07388 -0.0382 0.0359 1.0000
15.000 1.3417 0.08419 0.07920 -0.0379 0.0359 1.0000
15.250 1.3206 0.08927 0.08450 -0.0382 0.0359 1.0000
15.500 1.2963 0.09510 0.09056 -0.0393 0.0359 1.0000
15.750 1.2750 0.10071 0.09638 -0.0412 0.0361 1.0000
16.000 1.2498 0.10745 0.10332 -0.0441 0.0362 1.0000
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