FX 83-W-108 (fx83w108-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 83-W-108 (fx83w108-il) Reynolds number: 1,000,000 Max Cl/Cd: 157.23 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx83w108-il-1000000.txt Download as CSV file: xf-fx83w108-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3764 0.12086 0.11912 -0.0412 1.0000 0.0180
-11.500 -0.3831 0.11491 0.11319 -0.0436 1.0000 0.0194
-11.250 -0.6678 0.03329 0.03080 -0.1123 0.9845 0.0143
-11.000 -0.6483 0.02812 0.02522 -0.1205 0.9797 0.0144
-10.750 -0.6279 0.02578 0.02266 -0.1229 0.9728 0.0147
-10.500 -0.6024 0.02310 0.01969 -0.1261 0.9688 0.0148
-10.250 -0.5779 0.02159 0.01798 -0.1273 0.9613 0.0151
-10.000 -0.5462 0.01997 0.01616 -0.1300 0.9574 0.0152
-9.750 -0.5125 0.01873 0.01474 -0.1326 0.9531 0.0154
-9.500 -0.4805 0.01694 0.01273 -0.1352 0.9467 0.0156
-9.250 -0.4472 0.01496 0.01052 -0.1381 0.9407 0.0162
-9.000 -0.4149 0.01419 0.00965 -0.1398 0.9322 0.0166
-8.750 -0.3816 0.01367 0.00905 -0.1414 0.9243 0.0171
-8.500 -0.3517 0.01322 0.00852 -0.1423 0.9149 0.0176
-8.250 -0.3241 0.01277 0.00797 -0.1426 0.9060 0.0181
-8.000 -0.2966 0.01231 0.00738 -0.1428 0.8975 0.0186
-7.750 -0.2720 0.01185 0.00683 -0.1424 0.8888 0.0190
-7.250 -0.2223 0.01087 0.00564 -0.1416 0.8730 0.0201
-6.750 -0.1718 0.01014 0.00479 -0.1409 0.8593 0.0221
-6.500 -0.1457 0.00990 0.00449 -0.1406 0.8528 0.0231
-6.250 -0.1194 0.00971 0.00424 -0.1403 0.8470 0.0242
-6.000 -0.0945 0.00929 0.00375 -0.1398 0.8408 0.0261
-5.750 -0.0679 0.00910 0.00352 -0.1396 0.8353 0.0281
-5.500 -0.0414 0.00896 0.00336 -0.1393 0.8300 0.0299
-5.250 -0.0154 0.00868 0.00302 -0.1390 0.8246 0.0323
-5.000 0.0113 0.00850 0.00281 -0.1387 0.8195 0.0351
-4.750 0.0380 0.00837 0.00266 -0.1385 0.8149 0.0374
-4.500 0.0644 0.00815 0.00240 -0.1382 0.8100 0.0410
-4.250 0.0913 0.00802 0.00225 -0.1380 0.8054 0.0452
-4.000 0.1182 0.00786 0.00208 -0.1377 0.8010 0.0511
-3.750 0.1449 0.00771 0.00195 -0.1375 0.7966 0.0582
-3.500 0.1714 0.00750 0.00178 -0.1372 0.7921 0.0756
-3.250 0.1980 0.00729 0.00165 -0.1370 0.7878 0.1074
-3.000 0.2236 0.00698 0.00153 -0.1367 0.7838 0.1590
-2.750 0.2495 0.00672 0.00143 -0.1363 0.7795 0.2122
-2.500 0.2760 0.00657 0.00137 -0.1361 0.7754 0.2546
-2.250 0.3029 0.00645 0.00134 -0.1359 0.7714 0.2915
-2.000 0.3297 0.00636 0.00132 -0.1356 0.7674 0.3177
-1.750 0.3568 0.00631 0.00131 -0.1354 0.7631 0.3397
-1.500 0.3841 0.00630 0.00130 -0.1352 0.7588 0.3587
-1.250 0.4113 0.00627 0.00130 -0.1350 0.7546 0.3776
-1.000 0.4384 0.00624 0.00130 -0.1348 0.7504 0.3922
-0.750 0.4656 0.00622 0.00130 -0.1345 0.7464 0.4081
-0.500 0.4931 0.00624 0.00132 -0.1344 0.7424 0.4239
-0.250 0.5201 0.00621 0.00134 -0.1342 0.7386 0.4385
0.000 0.5471 0.00618 0.00135 -0.1339 0.7345 0.4528
0.250 0.5741 0.00617 0.00137 -0.1336 0.7303 0.4659
0.500 0.6013 0.00619 0.00139 -0.1334 0.7257 0.4788
0.750 0.6277 0.00615 0.00142 -0.1330 0.7208 0.4951
1.000 0.6541 0.00613 0.00144 -0.1326 0.7152 0.5131
1.250 0.6801 0.00613 0.00147 -0.1322 0.7086 0.5344
1.500 0.7052 0.00608 0.00149 -0.1315 0.7002 0.5611
1.750 0.7304 0.00605 0.00154 -0.1308 0.6925 0.5966
2.000 0.7544 0.00599 0.00158 -0.1299 0.6824 0.6406
2.250 0.7773 0.00591 0.00164 -0.1287 0.6695 0.6982
2.500 0.7990 0.00578 0.00172 -0.1273 0.6606 0.7796
2.750 0.8535 0.00551 0.00183 -0.1332 0.6482 1.0000
3.000 0.8780 0.00562 0.00189 -0.1325 0.6348 1.0000
3.250 0.9020 0.00575 0.00196 -0.1316 0.6166 1.0000
3.500 0.9261 0.00589 0.00205 -0.1307 0.5990 1.0000
3.750 0.9485 0.00609 0.00215 -0.1295 0.5749 1.0000
4.000 0.9707 0.00632 0.00228 -0.1283 0.5488 1.0000
4.250 0.9910 0.00664 0.00246 -0.1267 0.5141 1.0000
4.750 1.0250 0.00766 0.00300 -0.1224 0.4103 1.0000
5.000 1.0381 0.00841 0.00340 -0.1196 0.3405 1.0000
5.250 1.0528 0.00909 0.00380 -0.1171 0.2832 1.0000
5.500 1.0657 0.00986 0.00424 -0.1144 0.2206 1.0000
5.750 1.0817 0.01047 0.00462 -0.1123 0.1784 1.0000
6.000 1.0990 0.01100 0.00498 -0.1104 0.1463 1.0000
6.250 1.1162 0.01152 0.00535 -0.1085 0.1192 1.0000
6.500 1.1340 0.01196 0.00570 -0.1066 0.1004 1.0000
6.750 1.1510 0.01241 0.00606 -0.1046 0.0840 1.0000
7.000 1.1693 0.01281 0.00641 -0.1029 0.0724 1.0000
7.250 1.1875 0.01325 0.00678 -0.1012 0.0622 1.0000
7.500 1.2055 0.01369 0.00719 -0.0995 0.0538 1.0000
7.750 1.2243 0.01412 0.00759 -0.0980 0.0483 1.0000
8.000 1.2429 0.01456 0.00803 -0.0965 0.0433 1.0000
8.250 1.2619 0.01499 0.00845 -0.0950 0.0400 1.0000
8.500 1.2787 0.01556 0.00901 -0.0933 0.0357 1.0000
8.750 1.2984 0.01595 0.00943 -0.0921 0.0343 1.0000
9.000 1.3164 0.01646 0.00994 -0.0906 0.0319 1.0000
9.250 1.3312 0.01718 0.01065 -0.0887 0.0289 1.0000
9.500 1.3495 0.01768 0.01120 -0.0874 0.0277 1.0000
9.750 1.3675 0.01821 0.01177 -0.0861 0.0263 1.0000
10.000 1.3838 0.01886 0.01243 -0.0846 0.0248 1.0000
10.250 1.3964 0.01977 0.01337 -0.0826 0.0230 1.0000
10.500 1.4099 0.02064 0.01430 -0.0808 0.0223 1.0000
10.750 1.4271 0.02126 0.01496 -0.0796 0.0218 1.0000
11.000 1.4429 0.02198 0.01574 -0.0782 0.0210 1.0000
11.250 1.4571 0.02282 0.01663 -0.0767 0.0204 1.0000
11.500 1.4719 0.02364 0.01748 -0.0753 0.0197 1.0000
11.750 1.4844 0.02463 0.01851 -0.0738 0.0192 1.0000
12.000 1.4942 0.02584 0.01977 -0.0720 0.0184 1.0000
12.250 1.4989 0.02747 0.02148 -0.0697 0.0177 1.0000
12.500 1.5105 0.02858 0.02267 -0.0683 0.0175 1.0000
12.750 1.5302 0.02905 0.02316 -0.0677 0.0169 1.0000
13.000 1.5371 0.03058 0.02478 -0.0659 0.0167 1.0000
13.250 1.5513 0.03151 0.02575 -0.0649 0.0162 1.0000
13.500 1.5617 0.03275 0.02705 -0.0636 0.0158 1.0000
13.750 1.5698 0.03421 0.02858 -0.0622 0.0155 1.0000
14.000 1.5802 0.03550 0.02991 -0.0610 0.0151 1.0000
14.250 1.5867 0.03715 0.03163 -0.0596 0.0148 1.0000
14.500 1.5900 0.03910 0.03364 -0.0581 0.0144 1.0000
14.750 1.5881 0.04161 0.03625 -0.0564 0.0140 1.0000
15.000 1.5862 0.04419 0.03895 -0.0549 0.0137 1.0000
15.250 1.5916 0.04612 0.04096 -0.0539 0.0137 1.0000
15.500 1.5998 0.04779 0.04271 -0.0531 0.0135 1.0000
15.750 1.6046 0.04987 0.04488 -0.0523 0.0133 1.0000
16.000 1.6088 0.05206 0.04717 -0.0516 0.0130 1.0000
16.250 1.6103 0.05461 0.04981 -0.0509 0.0128 1.0000
16.500 1.6145 0.05688 0.05216 -0.0504 0.0126 1.0000
16.750 1.6155 0.05958 0.05494 -0.0500 0.0124 1.0000
17.000 1.6185 0.06211 0.05756 -0.0497 0.0121 1.0000
17.250 1.6177 0.06516 0.06070 -0.0496 0.0119 1.0000
17.500 1.6166 0.06833 0.06396 -0.0496 0.0117 1.0000
17.750 1.6149 0.07165 0.06735 -0.0497 0.0115 1.0000
18.000 1.6108 0.07533 0.07111 -0.0501 0.0112 1.0000
18.250 1.6009 0.07991 0.07580 -0.0506 0.0111 1.0000
18.500 1.5875 0.08510 0.08111 -0.0516 0.0108 1.0000
18.750 1.5707 0.09092 0.08707 -0.0528 0.0107 1.0000
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