WORTMANN FX 082-512 AIRFOIL (fx082512-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WORTMANN FX 082-512 AIRFOIL (fx082512-il) Reynolds number: 100,000 Max Cl/Cd: 47.66 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-fx082512-il-100000-n5.txt Download as CSV file: xf-fx082512-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WORTMANN FX 082-512 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6350 0.08894 0.08361 -0.0569 1.0000 0.0311
-12.000 -0.6628 0.08117 0.07576 -0.0606 1.0000 0.0309
-11.750 -0.6883 0.07476 0.06925 -0.0634 1.0000 0.0308
-11.500 -0.7118 0.06922 0.06360 -0.0654 1.0000 0.0308
-11.250 -0.7319 0.06465 0.05890 -0.0663 1.0000 0.0309
-11.000 -0.7508 0.06062 0.05475 -0.0666 1.0000 0.0311
-10.500 -0.7790 0.05521 0.04927 -0.0646 1.0000 0.0318
-10.250 -0.7939 0.05299 0.04704 -0.0627 1.0000 0.0321
-10.000 -0.8010 0.05055 0.04457 -0.0627 1.0000 0.0327
-9.750 -0.8022 0.04786 0.04181 -0.0638 1.0000 0.0336
-9.500 -0.7980 0.04498 0.03879 -0.0657 1.0000 0.0352
-9.250 -0.7891 0.04201 0.03556 -0.0676 1.0000 0.0380
-9.000 -0.7706 0.03965 0.03311 -0.0722 1.0000 0.0404
-8.750 -0.7522 0.03742 0.03063 -0.0744 1.0000 0.0445
-8.500 -0.7300 0.03564 0.02864 -0.0772 1.0000 0.0490
-8.250 -0.7054 0.03409 0.02685 -0.0801 1.0000 0.0545
-8.000 -0.6811 0.03257 0.02511 -0.0820 1.0000 0.0607
-7.750 -0.6549 0.03127 0.02356 -0.0843 1.0000 0.0677
-7.500 -0.6251 0.03021 0.02237 -0.0862 0.9986 0.0739
-7.250 -0.5917 0.02922 0.02117 -0.0891 0.9966 0.0814
-7.000 -0.5594 0.02845 0.02027 -0.0913 0.9948 0.0886
-6.750 -0.5326 0.02803 0.01997 -0.0912 0.9924 0.0926
-6.500 -0.5017 0.02762 0.01945 -0.0924 0.9898 0.0968
-6.250 -0.4700 0.02723 0.01911 -0.0939 0.9875 0.1011
-6.000 -0.4348 0.02679 0.01854 -0.0963 0.9855 0.1045
-5.750 -0.3987 0.02595 0.01762 -0.0996 0.9833 0.1081
-5.500 -0.3610 0.02502 0.01655 -0.1033 0.9810 0.1133
-5.250 -0.3203 0.02389 0.01527 -0.1080 0.9793 0.1200
-5.000 -0.2784 0.02271 0.01397 -0.1129 0.9778 0.1310
-4.750 -0.2399 0.02247 0.01460 -0.1164 0.9758 0.2582
-4.500 -0.2046 0.02252 0.01436 -0.1183 0.9731 0.2875
-4.250 -0.1744 0.02272 0.01434 -0.1190 0.9690 0.3018
-4.000 -0.1427 0.02312 0.01463 -0.1198 0.9653 0.3121
-3.750 -0.1078 0.02338 0.01471 -0.1214 0.9625 0.3215
-3.500 -0.0795 0.02370 0.01497 -0.1215 0.9583 0.3290
-3.250 -0.0489 0.02382 0.01497 -0.1223 0.9540 0.3357
-3.000 -0.0174 0.02406 0.01518 -0.1230 0.9505 0.3406
-2.750 0.0198 0.02399 0.01492 -0.1254 0.9481 0.3473
-2.500 0.0466 0.02414 0.01509 -0.1252 0.9432 0.3514
-2.250 0.0749 0.02430 0.01527 -0.1254 0.9384 0.3565
-2.000 0.1107 0.02423 0.01505 -0.1275 0.9352 0.3631
-1.750 0.1448 0.02428 0.01515 -0.1287 0.9325 0.3672
-1.500 0.1706 0.02437 0.01528 -0.1285 0.9270 0.3713
-1.250 0.2013 0.02433 0.01520 -0.1294 0.9220 0.3761
-1.000 0.2380 0.02416 0.01489 -0.1317 0.9188 0.3804
-0.750 0.2737 0.02400 0.01478 -0.1333 0.9160 0.3823
-0.500 0.3001 0.02394 0.01476 -0.1334 0.9101 0.3839
-0.250 0.3305 0.02386 0.01472 -0.1341 0.9048 0.3860
0.000 0.3657 0.02372 0.01461 -0.1357 0.9013 0.3885
0.250 0.4051 0.02348 0.01440 -0.1380 0.8985 0.3913
0.500 0.4310 0.02333 0.01426 -0.1378 0.8882 0.3936
0.750 0.4792 0.02259 0.01352 -0.1412 0.8823 0.3963
1.000 0.5097 0.02215 0.01315 -0.1413 0.8699 0.3981
1.250 0.5460 0.02161 0.01272 -0.1424 0.8613 0.4001
1.500 0.5800 0.02116 0.01240 -0.1431 0.8523 0.4023
1.750 0.6120 0.02066 0.01201 -0.1432 0.8393 0.4052
2.000 0.6481 0.01988 0.01132 -0.1438 0.8213 0.4085
2.250 0.6839 0.01920 0.01068 -0.1443 0.7987 0.4119
2.500 0.7177 0.01872 0.01028 -0.1447 0.7736 0.4147
2.750 0.7566 0.01819 0.00984 -0.1459 0.7416 0.4172
3.000 0.8105 0.01760 0.00913 -0.1498 0.6737 0.4207
3.250 0.8551 0.01794 0.00884 -0.1522 0.5391 0.4243
3.500 0.8693 0.01927 0.00926 -0.1495 0.3818 0.4271
3.750 0.8803 0.02100 0.01001 -0.1468 0.2081 0.4300
4.000 0.8964 0.02232 0.01079 -0.1450 0.1305 0.4326
4.500 0.9393 0.02355 0.01214 -0.1427 0.1157 0.4395
4.750 0.9603 0.02418 0.01285 -0.1414 0.1106 0.4433
5.000 0.9792 0.02495 0.01365 -0.1399 0.1062 0.4468
5.250 0.9985 0.02560 0.01447 -0.1383 0.1026 0.4499
5.500 1.0157 0.02650 0.01544 -0.1365 0.0984 0.4536
5.750 1.0348 0.02733 0.01636 -0.1350 0.0924 0.4580
6.000 1.0546 0.02822 0.01730 -0.1337 0.0860 0.4631
6.250 1.0749 0.02910 0.01831 -0.1325 0.0791 0.4679
6.500 1.0961 0.03008 0.01935 -0.1315 0.0726 0.4739
6.750 1.1175 0.03095 0.02040 -0.1304 0.0653 0.4805
7.000 1.1388 0.03189 0.02157 -0.1293 0.0580 0.4869
7.250 1.1587 0.03277 0.02255 -0.1281 0.0523 0.4947
7.500 1.1778 0.03351 0.02347 -0.1266 0.0471 0.5028
7.750 1.1981 0.03438 0.02455 -0.1254 0.0420 0.5137
8.000 1.2216 0.03569 0.02607 -0.1247 0.0382 0.5275
8.250 1.2392 0.03655 0.02708 -0.1232 0.0356 0.5450
8.500 1.2649 0.03824 0.02911 -0.1229 0.0322 0.5717
8.750 1.2840 0.03946 0.03063 -0.1216 0.0301 0.6146
9.250 1.3087 0.04214 0.03415 -0.1162 0.0279 1.0000
9.500 1.3341 0.04615 0.03872 -0.1160 0.0261 1.0000
9.750 1.3459 0.04973 0.04277 -0.1138 0.0245 1.0000
10.000 1.3500 0.05321 0.04666 -0.1108 0.0235 1.0000
10.250 1.3477 0.05697 0.05082 -0.1071 0.0230 1.0000
10.500 1.3398 0.06082 0.05505 -0.1032 0.0226 1.0000
10.750 1.3273 0.06487 0.05946 -0.0992 0.0223 1.0000
11.000 1.3110 0.06918 0.06410 -0.0956 0.0222 1.0000
11.250 1.2914 0.07389 0.06914 -0.0926 0.0221 1.0000
11.500 1.2689 0.07906 0.07462 -0.0905 0.0221 1.0000
11.750 1.2431 0.08496 0.08080 -0.0896 0.0221 1.0000
12.000 1.2140 0.09181 0.08793 -0.0902 0.0223 1.0000
12.250 1.1828 0.09981 0.09617 -0.0928 0.0225 1.0000
12.500 1.1480 0.10983 0.10641 -0.0983 0.0228 1.0000
12.750 1.1098 0.12344 0.12021 -0.1077 0.0235 1.0000
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Polar data table (+)
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