FX 83-W-108 (fx83w108-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: FX 83-W-108 (fx83w108-il) Reynolds number: 500,000 Max Cl/Cd: 117.7 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx83w108-il-500000-n5.txt Download as CSV file: xf-fx83w108-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6828 0.05031 0.04749 -0.0827 0.9942 0.0130
-11.500 -0.7002 0.03474 0.03141 -0.1079 0.9779 0.0129
-11.250 -0.6839 0.03083 0.02722 -0.1141 0.9685 0.0131
-11.000 -0.6656 0.02821 0.02436 -0.1171 0.9594 0.0133
-10.750 -0.6391 0.02622 0.02216 -0.1202 0.9543 0.0136
-10.500 -0.6138 0.02423 0.01993 -0.1226 0.9473 0.0138
-10.250 -0.5816 0.02262 0.01810 -0.1257 0.9431 0.0142
-10.000 -0.5502 0.02117 0.01642 -0.1283 0.9376 0.0146
-9.750 -0.5178 0.01990 0.01494 -0.1307 0.9318 0.0150
-9.500 -0.4836 0.01875 0.01357 -0.1332 0.9267 0.0153
-9.250 -0.4546 0.01761 0.01226 -0.1346 0.9184 0.0156
-9.000 -0.4231 0.01663 0.01115 -0.1364 0.9115 0.0161
-8.750 -0.3954 0.01596 0.01037 -0.1370 0.9032 0.0165
-8.500 -0.3658 0.01535 0.00965 -0.1380 0.8964 0.0169
-8.250 -0.3402 0.01483 0.00904 -0.1380 0.8883 0.0174
-7.750 -0.2876 0.01380 0.00778 -0.1381 0.8735 0.0185
-7.500 -0.2609 0.01337 0.00723 -0.1381 0.8667 0.0192
-7.250 -0.2358 0.01290 0.00667 -0.1378 0.8602 0.0198
-7.000 -0.2101 0.01248 0.00618 -0.1377 0.8539 0.0208
-6.750 -0.1836 0.01218 0.00582 -0.1376 0.8482 0.0219
-6.500 -0.1578 0.01190 0.00547 -0.1373 0.8419 0.0232
-6.250 -0.1313 0.01163 0.00511 -0.1371 0.8363 0.0244
-6.000 -0.1056 0.01125 0.00468 -0.1368 0.8310 0.0260
-5.750 -0.0794 0.01100 0.00439 -0.1366 0.8254 0.0277
-5.500 -0.0527 0.01078 0.00409 -0.1364 0.8204 0.0294
-5.250 -0.0263 0.01054 0.00380 -0.1362 0.8156 0.0313
-5.000 0.0000 0.01030 0.00355 -0.1359 0.8106 0.0340
-4.750 0.0269 0.01015 0.00334 -0.1358 0.8059 0.0371
-4.500 0.0536 0.00994 0.00310 -0.1355 0.8015 0.0407
-4.250 0.0801 0.00976 0.00292 -0.1353 0.7967 0.0451
-4.000 0.1069 0.00959 0.00272 -0.1351 0.7921 0.0504
-3.500 0.1606 0.00925 0.00239 -0.1347 0.7837 0.0683
-3.250 0.1872 0.00908 0.00224 -0.1344 0.7792 0.0838
-2.750 0.2401 0.00861 0.00197 -0.1340 0.7712 0.1549
-2.500 0.2663 0.00838 0.00188 -0.1338 0.7669 0.1986
-2.250 0.2927 0.00821 0.00182 -0.1336 0.7627 0.2394
-2.000 0.3195 0.00809 0.00177 -0.1333 0.7589 0.2778
-1.750 0.3463 0.00800 0.00176 -0.1331 0.7551 0.3115
-1.500 0.3732 0.00793 0.00176 -0.1329 0.7508 0.3371
-1.250 0.4002 0.00790 0.00175 -0.1327 0.7467 0.3595
-1.000 0.4273 0.00787 0.00176 -0.1324 0.7428 0.3818
-0.750 0.4542 0.00784 0.00177 -0.1322 0.7386 0.3997
-0.500 0.4810 0.00782 0.00178 -0.1319 0.7338 0.4146
-0.250 0.5080 0.00782 0.00178 -0.1316 0.7292 0.4267
0.000 0.5352 0.00783 0.00179 -0.1314 0.7253 0.4379
0.250 0.5620 0.00781 0.00183 -0.1311 0.7209 0.4491
0.500 0.5889 0.00780 0.00186 -0.1308 0.7165 0.4618
0.750 0.6158 0.00782 0.00188 -0.1306 0.7124 0.4746
1.000 0.6425 0.00781 0.00194 -0.1303 0.7081 0.4901
1.250 0.6688 0.00780 0.00199 -0.1299 0.7027 0.5066
1.500 0.6950 0.00781 0.00203 -0.1295 0.6973 0.5246
1.750 0.7208 0.00780 0.00210 -0.1289 0.6906 0.5463
2.000 0.7457 0.00779 0.00215 -0.1282 0.6817 0.5721
2.250 0.7697 0.00777 0.00221 -0.1273 0.6696 0.6031
2.500 0.7931 0.00774 0.00228 -0.1262 0.6569 0.6457
2.750 0.8146 0.00769 0.00237 -0.1248 0.6404 0.7030
3.000 0.8337 0.00761 0.00246 -0.1227 0.6216 0.7832
3.250 0.8804 0.00748 0.00258 -0.1268 0.5947 1.0000
3.500 0.9024 0.00769 0.00269 -0.1255 0.5711 1.0000
3.750 0.9224 0.00798 0.00284 -0.1239 0.5387 1.0000
4.000 0.9379 0.00848 0.00307 -0.1214 0.4853 1.0000
4.250 0.9543 0.00898 0.00334 -0.1191 0.4384 1.0000
4.500 0.9687 0.00962 0.00370 -0.1166 0.3814 1.0000
4.750 0.9818 0.01035 0.00412 -0.1139 0.3207 1.0000
5.000 0.9954 0.01108 0.00456 -0.1113 0.2652 1.0000
5.250 1.0113 0.01167 0.00495 -0.1091 0.2239 1.0000
5.500 1.0278 0.01223 0.00534 -0.1071 0.1898 1.0000
5.750 1.0444 0.01275 0.00572 -0.1051 0.1617 1.0000
6.000 1.0601 0.01326 0.00610 -0.1029 0.1367 1.0000
6.250 1.0759 0.01377 0.00650 -0.1007 0.1155 1.0000
6.500 1.0922 0.01426 0.00691 -0.0987 0.0981 1.0000
6.750 1.1085 0.01477 0.00734 -0.0967 0.0831 1.0000
7.000 1.1255 0.01524 0.00776 -0.0949 0.0718 1.0000
7.250 1.1425 0.01573 0.00821 -0.0931 0.0629 1.0000
7.500 1.1594 0.01624 0.00868 -0.0913 0.0559 1.0000
7.750 1.1773 0.01669 0.00915 -0.0897 0.0511 1.0000
8.000 1.1938 0.01723 0.00967 -0.0880 0.0457 1.0000
8.250 1.2111 0.01774 0.01019 -0.0864 0.0417 1.0000
8.500 1.2276 0.01830 0.01075 -0.0847 0.0380 1.0000
8.750 1.2437 0.01890 0.01136 -0.0831 0.0354 1.0000
9.000 1.2603 0.01948 0.01198 -0.0815 0.0335 1.0000
9.250 1.2762 0.02011 0.01264 -0.0799 0.0315 1.0000
9.500 1.2908 0.02085 0.01339 -0.0782 0.0296 1.0000
9.750 1.3056 0.02159 0.01417 -0.0766 0.0281 1.0000
10.000 1.3210 0.02230 0.01494 -0.0751 0.0269 1.0000
10.250 1.3358 0.02306 0.01576 -0.0736 0.0254 1.0000
10.500 1.3499 0.02390 0.01663 -0.0720 0.0242 1.0000
10.750 1.3626 0.02485 0.01761 -0.0704 0.0231 1.0000
11.000 1.3750 0.02584 0.01865 -0.0688 0.0221 1.0000
11.250 1.3881 0.02680 0.01969 -0.0673 0.0213 1.0000
11.500 1.4011 0.02778 0.02075 -0.0659 0.0206 1.0000
11.750 1.4129 0.02887 0.02190 -0.0645 0.0199 1.0000
12.000 1.4245 0.02998 0.02307 -0.0631 0.0192 1.0000
12.250 1.4352 0.03120 0.02434 -0.0617 0.0188 1.0000
12.500 1.4435 0.03263 0.02583 -0.0601 0.0182 1.0000
12.750 1.4507 0.03418 0.02744 -0.0585 0.0177 1.0000
13.000 1.4596 0.03562 0.02897 -0.0572 0.0173 1.0000
13.250 1.4679 0.03712 0.03058 -0.0559 0.0171 1.0000
13.500 1.4767 0.03859 0.03214 -0.0547 0.0166 1.0000
13.750 1.4839 0.04023 0.03387 -0.0534 0.0162 1.0000
14.000 1.4910 0.04192 0.03565 -0.0523 0.0159 1.0000
14.250 1.4972 0.04373 0.03755 -0.0512 0.0155 1.0000
14.500 1.5034 0.04556 0.03947 -0.0502 0.0152 1.0000
14.750 1.5080 0.04760 0.04158 -0.0493 0.0149 1.0000
15.000 1.5123 0.04972 0.04378 -0.0485 0.0145 1.0000
15.250 1.5146 0.05211 0.04626 -0.0477 0.0142 1.0000
15.500 1.5147 0.05479 0.04903 -0.0470 0.0137 1.0000
15.750 1.5193 0.05704 0.05140 -0.0465 0.0134 1.0000
16.000 1.5212 0.05964 0.05411 -0.0461 0.0132 1.0000
16.250 1.5218 0.06248 0.05707 -0.0457 0.0129 1.0000
16.500 1.5232 0.06529 0.05999 -0.0456 0.0126 1.0000
16.750 1.5223 0.06846 0.06328 -0.0456 0.0124 1.0000
17.000 1.5215 0.07169 0.06662 -0.0458 0.0121 1.0000
17.250 1.5167 0.07552 0.07058 -0.0461 0.0121 1.0000
17.500 1.5156 0.07898 0.07414 -0.0467 0.0117 1.0000
17.750 1.5112 0.08299 0.07827 -0.0474 0.0115 1.0000
18.000 1.5049 0.08737 0.08278 -0.0485 0.0114 1.0000
18.250 1.4972 0.09207 0.08760 -0.0498 0.0112 1.0000
18.500 1.4882 0.09709 0.09274 -0.0514 0.0111 1.0000
18.750 1.4776 0.10253 0.09830 -0.0533 0.0110 1.0000
19.000 1.4654 0.10839 0.10429 -0.0557 0.0108 1.0000
19.250 1.4528 0.11447 0.11051 -0.0583 0.0107 1.0000
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Polar data table (+)
Polar graphs
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