FX 83-W-108 (fx83w108-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 83-W-108 (fx83w108-il) Reynolds number: 200,000 Max Cl/Cd: 86.8 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx83w108-il-200000-n5.txt Download as CSV file: xf-fx83w108-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3733 0.10780 0.10398 -0.0474 1.0000 0.0232
-10.500 -0.3759 0.10451 0.10074 -0.0475 1.0000 0.0230
-10.250 -0.3869 0.09975 0.09604 -0.0482 1.0000 0.0237
-10.000 -0.3908 0.09598 0.09231 -0.0490 0.9994 0.0236
-9.750 -0.3842 0.08980 0.08614 -0.0545 0.9951 0.0235
-9.500 -0.3817 0.08290 0.07925 -0.0606 0.9899 0.0233
-9.250 -0.3854 0.07451 0.07088 -0.0682 0.9823 0.0232
-9.000 -0.4530 0.04149 0.03727 -0.1079 0.9524 0.0222
-8.750 -0.4419 0.03441 0.02950 -0.1158 0.9433 0.0225
-8.500 -0.4234 0.03031 0.02483 -0.1189 0.9358 0.0230
-8.250 -0.3976 0.02719 0.02118 -0.1216 0.9308 0.0236
-8.000 -0.3670 0.02481 0.01831 -0.1240 0.9275 0.0244
-7.750 -0.3426 0.02329 0.01662 -0.1246 0.9209 0.0251
-7.500 -0.3126 0.02239 0.01564 -0.1259 0.9163 0.0263
-7.250 -0.2801 0.02130 0.01437 -0.1277 0.9131 0.0275
-7.000 -0.2528 0.02019 0.01304 -0.1282 0.9075 0.0288
-6.750 -0.2242 0.01914 0.01177 -0.1287 0.9021 0.0299
-6.500 -0.1929 0.01805 0.01056 -0.1300 0.8982 0.0312
-6.250 -0.1651 0.01734 0.00981 -0.1304 0.8929 0.0328
-6.000 -0.1376 0.01680 0.00918 -0.1306 0.8873 0.0351
-5.750 -0.1067 0.01627 0.00850 -0.1315 0.8831 0.0378
-5.500 -0.0796 0.01558 0.00780 -0.1317 0.8778 0.0404
-5.250 -0.0530 0.01515 0.00731 -0.1316 0.8720 0.0433
-5.000 -0.0231 0.01476 0.00680 -0.1322 0.8678 0.0471
-4.750 0.0040 0.01423 0.00626 -0.1323 0.8629 0.0516
-4.500 0.0301 0.01392 0.00588 -0.1320 0.8572 0.0567
-4.250 0.0586 0.01351 0.00543 -0.1323 0.8528 0.0638
-4.000 0.0870 0.01318 0.00506 -0.1325 0.8485 0.0729
-3.750 0.1121 0.01287 0.00478 -0.1321 0.8429 0.0876
-3.500 0.1395 0.01252 0.00448 -0.1322 0.8382 0.1145
-3.000 0.1922 0.01179 0.00414 -0.1320 0.8290 0.2275
-2.750 0.2188 0.01159 0.00406 -0.1319 0.8243 0.2805
-2.500 0.2473 0.01147 0.00401 -0.1320 0.8205 0.3215
-2.250 0.2739 0.01143 0.00399 -0.1317 0.8160 0.3510
-2.000 0.3002 0.01141 0.00398 -0.1313 0.8110 0.3764
-1.750 0.3277 0.01136 0.00397 -0.1312 0.8069 0.4027
-1.500 0.3568 0.01133 0.00393 -0.1314 0.8034 0.4270
-1.250 0.3813 0.01132 0.00397 -0.1306 0.7981 0.4442
-1.000 0.4080 0.01130 0.00396 -0.1303 0.7936 0.4598
-0.750 0.4362 0.01127 0.00393 -0.1303 0.7897 0.4747
-0.500 0.4629 0.01126 0.00394 -0.1300 0.7854 0.4894
-0.250 0.4884 0.01125 0.00398 -0.1295 0.7804 0.5051
0.000 0.5155 0.01122 0.00399 -0.1292 0.7760 0.5222
0.250 0.5439 0.01119 0.00400 -0.1292 0.7724 0.5419
0.500 0.5678 0.01119 0.00410 -0.1283 0.7666 0.5632
0.750 0.5938 0.01115 0.00415 -0.1279 0.7618 0.5884
1.000 0.6215 0.01110 0.00418 -0.1277 0.7579 0.6200
1.250 0.6455 0.01107 0.00432 -0.1268 0.7527 0.6594
1.500 0.6695 0.01099 0.00443 -0.1258 0.7477 0.7133
1.750 0.6966 0.01081 0.00449 -0.1253 0.7434 0.7996
2.000 0.7433 0.01063 0.00455 -0.1292 0.7389 1.0000
2.250 0.7685 0.01074 0.00466 -0.1286 0.7325 1.0000
2.500 0.7967 0.01081 0.00469 -0.1285 0.7271 1.0000
2.750 0.8206 0.01091 0.00483 -0.1277 0.7186 1.0000
3.000 0.8474 0.01095 0.00482 -0.1272 0.7096 1.0000
3.250 0.8715 0.01100 0.00485 -0.1262 0.6975 1.0000
3.500 0.8950 0.01104 0.00489 -0.1251 0.6829 1.0000
3.750 0.9185 0.01109 0.00491 -0.1239 0.6663 1.0000
4.000 0.9415 0.01117 0.00496 -0.1227 0.6492 1.0000
4.250 0.9643 0.01129 0.00507 -0.1215 0.6318 1.0000
4.500 0.9866 0.01143 0.00520 -0.1202 0.6114 1.0000
4.750 1.0078 0.01161 0.00530 -0.1187 0.5846 1.0000
5.000 1.0270 0.01187 0.00543 -0.1168 0.5493 1.0000
5.250 1.0429 0.01229 0.00563 -0.1143 0.5025 1.0000
5.500 1.0528 0.01297 0.00597 -0.1107 0.4403 1.0000
5.750 1.0592 0.01384 0.00647 -0.1068 0.3744 1.0000
6.000 1.0647 0.01480 0.00708 -0.1028 0.3120 1.0000
6.250 1.0709 0.01571 0.00771 -0.0991 0.2601 1.0000
6.500 1.0779 0.01661 0.00836 -0.0955 0.2151 1.0000
6.750 1.0870 0.01748 0.00904 -0.0925 0.1789 1.0000
7.000 1.0983 0.01827 0.00970 -0.0899 0.1511 1.0000
7.250 1.1103 0.01907 0.01038 -0.0874 0.1287 1.0000
7.500 1.1224 0.01987 0.01110 -0.0850 0.1097 1.0000
7.750 1.1350 0.02068 0.01184 -0.0828 0.0952 1.0000
8.000 1.1480 0.02148 0.01262 -0.0808 0.0837 1.0000
8.250 1.1611 0.02230 0.01343 -0.0787 0.0743 1.0000
8.500 1.1730 0.02322 0.01430 -0.0766 0.0661 1.0000
8.750 1.1868 0.02402 0.01516 -0.0748 0.0603 1.0000
9.000 1.1977 0.02506 0.01616 -0.0728 0.0550 1.0000
9.250 1.2113 0.02592 0.01712 -0.0711 0.0512 1.0000
9.500 1.2234 0.02691 0.01816 -0.0693 0.0477 1.0000
9.750 1.2331 0.02811 0.01937 -0.0673 0.0449 1.0000
10.000 1.2450 0.02918 0.02052 -0.0656 0.0426 1.0000
10.250 1.2571 0.03025 0.02167 -0.0640 0.0400 1.0000
10.500 1.2678 0.03145 0.02294 -0.0624 0.0382 1.0000
10.750 1.2765 0.03284 0.02436 -0.0607 0.0363 1.0000
11.000 1.2861 0.03421 0.02581 -0.0591 0.0348 1.0000
11.250 1.2960 0.03558 0.02729 -0.0575 0.0334 1.0000
11.500 1.3056 0.03700 0.02880 -0.0561 0.0322 1.0000
11.750 1.3147 0.03849 0.03037 -0.0546 0.0311 1.0000
12.000 1.3229 0.04006 0.03202 -0.0532 0.0301 1.0000
12.250 1.3300 0.04179 0.03382 -0.0518 0.0293 1.0000
12.500 1.3359 0.04373 0.03582 -0.0504 0.0283 1.0000
12.750 1.3453 0.04531 0.03755 -0.0492 0.0274 1.0000
13.000 1.3532 0.04711 0.03949 -0.0480 0.0266 1.0000
13.250 1.3605 0.04896 0.04148 -0.0469 0.0258 1.0000
13.500 1.3670 0.05093 0.04357 -0.0458 0.0252 1.0000
13.750 1.3726 0.05300 0.04576 -0.0448 0.0246 1.0000
14.000 1.3775 0.05516 0.04803 -0.0439 0.0241 1.0000
14.250 1.3815 0.05746 0.05045 -0.0431 0.0236 1.0000
14.500 1.3849 0.05988 0.05297 -0.0423 0.0232 1.0000
14.750 1.3871 0.06255 0.05573 -0.0416 0.0228 1.0000
15.000 1.3879 0.06546 0.05880 -0.0410 0.0223 1.0000
15.250 1.3875 0.06849 0.06205 -0.0407 0.0220 1.0000
15.500 1.3848 0.07192 0.06570 -0.0406 0.0215 1.0000
15.750 1.3810 0.07560 0.06960 -0.0407 0.0212 1.0000
16.000 1.3756 0.07958 0.07379 -0.0411 0.0208 1.0000
16.250 1.3682 0.08396 0.07839 -0.0418 0.0204 1.0000
16.500 1.3602 0.08859 0.08323 -0.0429 0.0202 1.0000
16.750 1.3503 0.09371 0.08855 -0.0445 0.0199 1.0000
17.000 1.3390 0.09926 0.09430 -0.0465 0.0197 1.0000
17.250 1.3265 0.10521 0.10047 -0.0490 0.0195 1.0000
17.500 1.3127 0.11168 0.10713 -0.0522 0.0193 1.0000
17.750 1.2963 0.11899 0.11464 -0.0561 0.0192 1.0000
18.000 1.2787 0.12695 0.12280 -0.0607 0.0191 1.0000
18.250 1.2524 0.13745 0.13353 -0.0673 0.0191 1.0000
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