FX 83-W-108 (fx83w108-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: FX 83-W-108 (fx83w108-il) Reynolds number: 500,000 Max Cl/Cd: 129.6 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-fx83w108-il-500000.txt Download as CSV file: xf-fx83w108-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2208 0.08457 0.08237 -0.0652 0.9873 0.0326
-10.000 -0.2134 0.08057 0.07836 -0.0675 0.9842 0.0334
-9.750 -0.2070 0.07601 0.07380 -0.0704 0.9818 0.0343
-9.500 -0.4366 0.05720 0.05486 -0.0854 0.9846 0.0249
-9.250 -0.4309 0.04680 0.04432 -0.1025 0.9733 0.0237
-9.000 -0.4286 0.03376 0.03053 -0.1221 0.9602 0.0230
-8.750 -0.4067 0.02720 0.02330 -0.1288 0.9559 0.0228
-8.500 -0.3829 0.02414 0.01982 -0.1310 0.9488 0.0233
-8.250 -0.3513 0.02193 0.01725 -0.1336 0.9446 0.0239
-8.000 -0.3157 0.02032 0.01531 -0.1364 0.9416 0.0243
-7.750 -0.2911 0.01832 0.01303 -0.1368 0.9333 0.0247
-7.500 -0.2597 0.01631 0.01085 -0.1387 0.9287 0.0256
-7.250 -0.2313 0.01551 0.00996 -0.1393 0.9219 0.0264
-7.000 -0.2013 0.01482 0.00918 -0.1401 0.9155 0.0274
-6.750 -0.1716 0.01415 0.00839 -0.1408 0.9094 0.0286
-6.500 -0.1453 0.01362 0.00775 -0.1406 0.9021 0.0297
-6.250 -0.1161 0.01279 0.00679 -0.1412 0.8967 0.0315
-6.000 -0.0927 0.01232 0.00631 -0.1406 0.8892 0.0335
-5.750 -0.0647 0.01196 0.00588 -0.1407 0.8834 0.0358
-5.500 -0.0379 0.01168 0.00551 -0.1405 0.8775 0.0377
-5.250 -0.0138 0.01103 0.00482 -0.1400 0.8712 0.0409
-5.000 0.0147 0.01078 0.00450 -0.1402 0.8663 0.0443
-4.750 0.0403 0.01059 0.00427 -0.1397 0.8605 0.0476
-4.500 0.0659 0.01016 0.00382 -0.1393 0.8550 0.0531
-4.250 0.0946 0.01002 0.00360 -0.1395 0.8505 0.0579
-4.000 0.1193 0.00965 0.00326 -0.1389 0.8451 0.0675
-3.750 0.1455 0.00937 0.00299 -0.1386 0.8400 0.0821
-3.500 0.1724 0.00898 0.00273 -0.1385 0.8357 0.1252
-3.250 0.1969 0.00855 0.00258 -0.1381 0.8308 0.2032
-3.000 0.2225 0.00830 0.00250 -0.1378 0.8259 0.2641
-2.750 0.2498 0.00817 0.00245 -0.1377 0.8217 0.3058
-2.500 0.2774 0.00812 0.00244 -0.1376 0.8176 0.3352
-2.250 0.3037 0.00809 0.00243 -0.1372 0.8128 0.3590
-2.000 0.3309 0.00805 0.00241 -0.1370 0.8084 0.3800
-1.750 0.3592 0.00804 0.00240 -0.1370 0.8046 0.3995
-1.500 0.3857 0.00803 0.00242 -0.1367 0.8002 0.4164
-1.250 0.4123 0.00801 0.00242 -0.1363 0.7956 0.4335
-1.000 0.4398 0.00800 0.00242 -0.1361 0.7913 0.4520
-0.750 0.4678 0.00801 0.00243 -0.1361 0.7873 0.4684
-0.500 0.4934 0.00797 0.00245 -0.1355 0.7823 0.4839
-0.250 0.5203 0.00794 0.00245 -0.1353 0.7778 0.4989
0.000 0.5482 0.00793 0.00245 -0.1352 0.7739 0.5150
0.250 0.5746 0.00792 0.00250 -0.1348 0.7697 0.5330
0.500 0.6005 0.00787 0.00254 -0.1344 0.7650 0.5546
1.000 0.6543 0.00780 0.00264 -0.1338 0.7567 0.6185
1.250 0.6778 0.00769 0.00272 -0.1328 0.7512 0.6667
1.500 0.7015 0.00754 0.00278 -0.1317 0.7459 0.7375
1.750 0.7241 0.00729 0.00285 -0.1302 0.7406 0.8550
2.000 0.7783 0.00710 0.00283 -0.1360 0.7321 1.0000
2.250 0.8040 0.00715 0.00282 -0.1354 0.7237 1.0000
2.500 0.8284 0.00717 0.00281 -0.1344 0.7134 1.0000
2.750 0.8525 0.00720 0.00283 -0.1335 0.7026 1.0000
3.000 0.8773 0.00726 0.00285 -0.1327 0.6923 1.0000
3.250 0.9020 0.00733 0.00289 -0.1319 0.6820 1.0000
3.500 0.9261 0.00739 0.00296 -0.1310 0.6701 1.0000
3.750 0.9499 0.00747 0.00302 -0.1300 0.6565 1.0000
4.000 0.9732 0.00757 0.00309 -0.1289 0.6411 1.0000
4.250 0.9966 0.00769 0.00319 -0.1278 0.6258 1.0000
4.500 1.0184 0.00786 0.00329 -0.1265 0.6050 1.0000
4.750 1.0389 0.00807 0.00342 -0.1248 0.5771 1.0000
5.000 1.0576 0.00837 0.00360 -0.1229 0.5444 1.0000
5.250 1.0736 0.00880 0.00385 -0.1204 0.5007 1.0000
5.500 1.0856 0.00943 0.00420 -0.1173 0.4435 1.0000
5.750 1.0941 0.01027 0.00467 -0.1136 0.3746 1.0000
6.000 1.1014 0.01122 0.00524 -0.1099 0.3025 1.0000
6.250 1.1095 0.01214 0.00581 -0.1064 0.2405 1.0000
6.500 1.1182 0.01295 0.00636 -0.1029 0.1921 1.0000
6.750 1.1285 0.01373 0.00691 -0.0999 0.1509 1.0000
7.000 1.1409 0.01442 0.00744 -0.0972 0.1223 1.0000
7.250 1.1546 0.01508 0.00797 -0.0948 0.1012 1.0000
7.500 1.1690 0.01570 0.00852 -0.0926 0.0855 1.0000
7.750 1.1838 0.01633 0.00910 -0.0905 0.0734 1.0000
8.000 1.1981 0.01700 0.00973 -0.0884 0.0638 1.0000
8.250 1.2119 0.01771 0.01039 -0.0862 0.0565 1.0000
8.500 1.2274 0.01834 0.01105 -0.0843 0.0519 1.0000
8.750 1.2425 0.01901 0.01173 -0.0825 0.0483 1.0000
9.000 1.2526 0.02000 0.01274 -0.0800 0.0442 1.0000
9.250 1.2695 0.02059 0.01339 -0.0786 0.0420 1.0000
9.500 1.2840 0.02134 0.01417 -0.0769 0.0394 1.0000
9.750 1.2942 0.02242 0.01525 -0.0747 0.0368 1.0000
10.000 1.3049 0.02349 0.01639 -0.0726 0.0350 1.0000
10.250 1.3193 0.02432 0.01729 -0.0711 0.0332 1.0000
10.500 1.3319 0.02530 0.01831 -0.0694 0.0319 1.0000
10.750 1.3433 0.02638 0.01943 -0.0677 0.0307 1.0000
11.000 1.3482 0.02801 0.02111 -0.0653 0.0291 1.0000
11.250 1.3542 0.02963 0.02281 -0.0631 0.0282 1.0000
11.500 1.3667 0.03072 0.02398 -0.0617 0.0276 1.0000
11.750 1.3773 0.03200 0.02536 -0.0602 0.0270 1.0000
12.000 1.3878 0.03330 0.02674 -0.0587 0.0262 1.0000
12.250 1.3978 0.03464 0.02816 -0.0572 0.0257 1.0000
12.500 1.4073 0.03605 0.02963 -0.0558 0.0249 1.0000
12.750 1.4164 0.03750 0.03114 -0.0545 0.0243 1.0000
13.000 1.4237 0.03913 0.03282 -0.0530 0.0236 1.0000
13.250 1.4289 0.04107 0.03483 -0.0513 0.0231 1.0000
13.500 1.4326 0.04345 0.03733 -0.0493 0.0225 1.0000
13.750 1.4404 0.04506 0.03906 -0.0482 0.0222 1.0000
14.000 1.4475 0.04675 0.04087 -0.0471 0.0218 1.0000
14.250 1.4535 0.04868 0.04293 -0.0459 0.0215 1.0000
14.500 1.4590 0.05058 0.04493 -0.0450 0.0209 1.0000
14.750 1.4630 0.05272 0.04720 -0.0440 0.0205 1.0000
15.000 1.4664 0.05493 0.04951 -0.0433 0.0200 1.0000
15.250 1.4697 0.05719 0.05186 -0.0427 0.0196 1.0000
15.500 1.4725 0.05954 0.05429 -0.0423 0.0191 1.0000
15.750 1.4747 0.06204 0.05683 -0.0421 0.0186 1.0000
16.000 1.4737 0.06499 0.05987 -0.0416 0.0182 1.0000
16.250 1.4660 0.06889 0.06391 -0.0408 0.0178 1.0000
16.500 1.4605 0.07264 0.06783 -0.0408 0.0176 1.0000
16.750 1.4564 0.07634 0.07170 -0.0412 0.0174 1.0000
17.000 1.4522 0.08018 0.07569 -0.0419 0.0172 1.0000
17.250 1.4438 0.08469 0.08039 -0.0426 0.0170 1.0000
17.500 1.4374 0.08913 0.08497 -0.0439 0.0167 1.0000
17.750 1.4290 0.09400 0.09000 -0.0454 0.0165 1.0000
18.000 1.4183 0.09941 0.09558 -0.0474 0.0163 1.0000
18.250 1.4070 0.10510 0.10142 -0.0497 0.0161 1.0000
18.500 1.3960 0.11092 0.10740 -0.0524 0.0159 1.0000
18.750 1.3814 0.11760 0.11424 -0.0557 0.0158 1.0000
19.000 1.3662 0.12467 0.12147 -0.0595 0.0156 1.0000
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Polar data table (+)
Polar graphs
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