Ornithopter airfoil. (s1020-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: Ornithopter airfoil. (s1020-il) Reynolds number: 200,000 Max Cl/Cd: 81.49 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1020-il-200000-n5.txt Download as CSV file: xf-s1020-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Ornithopter airfoil.
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.1942 0.09034 0.08661 -0.0974 0.9557 0.0185
-10.250 -0.1934 0.08421 0.08048 -0.1019 0.9514 0.0182
-10.000 -0.2040 0.07657 0.07288 -0.1063 0.9439 0.0179
-9.750 -0.2616 0.05568 0.05180 -0.1231 0.9332 0.0170
-9.500 -0.2932 0.04599 0.04176 -0.1341 0.9212 0.0165
-9.250 -0.3060 0.04075 0.03614 -0.1385 0.9100 0.0165
-9.000 -0.3079 0.03695 0.03195 -0.1396 0.9003 0.0165
-8.750 -0.2919 0.03343 0.02799 -0.1423 0.8957 0.0166
-8.500 -0.2770 0.03084 0.02503 -0.1430 0.8892 0.0167
-8.250 -0.2560 0.02858 0.02242 -0.1440 0.8837 0.0170
-8.000 -0.2267 0.02652 0.02002 -0.1461 0.8804 0.0173
-7.750 -0.2035 0.02510 0.01833 -0.1464 0.8748 0.0180
-7.500 -0.1783 0.02380 0.01675 -0.1468 0.8693 0.0187
-7.250 -0.1459 0.02251 0.01519 -0.1485 0.8657 0.0191
-7.000 -0.1195 0.02132 0.01386 -0.1489 0.8606 0.0194
-6.750 -0.0958 0.02023 0.01271 -0.1488 0.8545 0.0198
-6.500 -0.0644 0.01924 0.01163 -0.1502 0.8505 0.0203
-6.250 -0.0388 0.01851 0.01082 -0.1502 0.8449 0.0208
-6.000 -0.0135 0.01783 0.01007 -0.1502 0.8388 0.0214
-5.750 0.0182 0.01712 0.00924 -0.1515 0.8346 0.0224
-5.500 0.0422 0.01660 0.00863 -0.1511 0.8283 0.0232
-5.250 0.0693 0.01609 0.00801 -0.1514 0.8226 0.0245
-5.000 0.1017 0.01556 0.00740 -0.1527 0.8185 0.0274
-4.750 0.1244 0.01524 0.00700 -0.1519 0.8117 0.0298
-4.500 0.1529 0.01479 0.00650 -0.1524 0.8063 0.0344
-4.250 0.1830 0.01430 0.00601 -0.1532 0.8016 0.0500
-4.000 0.2063 0.01385 0.00570 -0.1527 0.7950 0.0874
-3.750 0.2349 0.01329 0.00537 -0.1535 0.7899 0.1555
-3.500 0.2616 0.01273 0.00515 -0.1539 0.7845 0.2489
-3.250 0.2866 0.01237 0.00506 -0.1538 0.7783 0.3315
-3.000 0.3164 0.01217 0.00500 -0.1544 0.7734 0.4015
-2.750 0.3419 0.01213 0.00500 -0.1540 0.7674 0.4423
-2.500 0.3691 0.01211 0.00495 -0.1539 0.7615 0.4690
-2.250 0.3997 0.01207 0.00485 -0.1545 0.7569 0.4896
-2.000 0.4235 0.01209 0.00486 -0.1537 0.7501 0.5068
-1.750 0.4516 0.01208 0.00481 -0.1538 0.7446 0.5234
-1.500 0.4795 0.01209 0.00477 -0.1538 0.7392 0.5384
-1.250 0.5047 0.01211 0.00477 -0.1533 0.7326 0.5524
-1.000 0.5337 0.01211 0.00471 -0.1536 0.7274 0.5663
-0.750 0.5588 0.01213 0.00474 -0.1530 0.7211 0.5784
-0.500 0.5854 0.01215 0.00474 -0.1528 0.7150 0.5902
-0.250 0.6136 0.01217 0.00471 -0.1529 0.7097 0.6026
0.000 0.6379 0.01222 0.00477 -0.1523 0.7029 0.6153
0.250 0.6656 0.01224 0.00477 -0.1523 0.6973 0.6276
0.500 0.6906 0.01228 0.00483 -0.1518 0.6909 0.6401
0.750 0.7163 0.01232 0.00488 -0.1514 0.6845 0.6531
1.000 0.7434 0.01237 0.00491 -0.1513 0.6789 0.6667
1.250 0.7672 0.01243 0.00501 -0.1505 0.6719 0.6808
1.750 0.8175 0.01255 0.00517 -0.1496 0.6594 0.7107
2.000 0.8424 0.01261 0.00526 -0.1490 0.6529 0.7269
2.250 0.8668 0.01268 0.00536 -0.1483 0.6466 0.7441
2.500 0.8897 0.01275 0.00548 -0.1474 0.6397 0.7623
2.750 0.9144 0.01281 0.00556 -0.1467 0.6337 0.7822
3.000 0.9349 0.01289 0.00573 -0.1453 0.6263 0.8049
3.250 0.9582 0.01295 0.00581 -0.1443 0.6201 0.8300
3.500 0.9770 0.01300 0.00596 -0.1424 0.6128 0.8619
3.750 0.9980 0.01302 0.00604 -0.1409 0.6061 0.9104
4.000 1.0260 0.01308 0.00614 -0.1412 0.5989 1.0000
4.250 1.0507 0.01326 0.00629 -0.1408 0.5917 1.0000
4.500 1.0746 0.01346 0.00647 -0.1403 0.5846 1.0000
4.750 1.0979 0.01366 0.00667 -0.1396 0.5769 1.0000
5.000 1.1209 0.01386 0.00687 -0.1389 0.5696 1.0000
5.250 1.1423 0.01407 0.00707 -0.1378 0.5617 1.0000
5.500 1.1636 0.01429 0.00731 -0.1367 0.5539 1.0000
5.750 1.1841 0.01453 0.00754 -0.1355 0.5456 1.0000
6.000 1.2040 0.01478 0.00781 -0.1342 0.5373 1.0000
6.250 1.2245 0.01505 0.00807 -0.1330 0.5290 1.0000
6.500 1.2432 0.01533 0.00840 -0.1315 0.5204 1.0000
6.750 1.2631 0.01562 0.00868 -0.1302 0.5120 1.0000
7.000 1.2804 0.01594 0.00905 -0.1285 0.5026 1.0000
7.250 1.2987 0.01627 0.00940 -0.1269 0.4938 1.0000
7.500 1.3154 0.01663 0.00979 -0.1252 0.4839 1.0000
7.750 1.3314 0.01701 0.01021 -0.1233 0.4737 1.0000
8.000 1.3470 0.01742 0.01064 -0.1214 0.4635 1.0000
8.250 1.3613 0.01788 0.01111 -0.1193 0.4523 1.0000
8.500 1.3749 0.01836 0.01166 -0.1171 0.4406 1.0000
8.750 1.3878 0.01890 0.01222 -0.1149 0.4285 1.0000
9.000 1.3988 0.01951 0.01285 -0.1124 0.4149 1.0000
9.250 1.4088 0.02019 0.01354 -0.1098 0.4006 1.0000
9.500 1.4167 0.02098 0.01433 -0.1071 0.3840 1.0000
9.750 1.4219 0.02193 0.01526 -0.1041 0.3650 1.0000
10.000 1.4235 0.02311 0.01637 -0.1007 0.3421 1.0000
10.250 1.4235 0.02448 0.01764 -0.0974 0.3180 1.0000
10.500 1.4217 0.02607 0.01913 -0.0941 0.2919 1.0000
10.750 1.4196 0.02780 0.02076 -0.0910 0.2677 1.0000
11.000 1.4148 0.02985 0.02268 -0.0879 0.2413 1.0000
11.250 1.4151 0.03169 0.02447 -0.0855 0.2207 1.0000
11.500 1.4128 0.03381 0.02651 -0.0831 0.1995 1.0000
11.750 1.4116 0.03597 0.02862 -0.0810 0.1794 1.0000
12.000 1.4102 0.03826 0.03085 -0.0790 0.1601 1.0000
12.250 1.4070 0.04079 0.03330 -0.0772 0.1405 1.0000
12.500 1.4044 0.04338 0.03583 -0.0756 0.1214 1.0000
12.750 1.4004 0.04622 0.03859 -0.0741 0.1032 1.0000
13.000 1.3989 0.04893 0.04126 -0.0728 0.0882 1.0000
13.250 1.3972 0.05174 0.04406 -0.0718 0.0745 1.0000
13.500 1.3950 0.05470 0.04699 -0.0709 0.0619 1.0000
13.750 1.3924 0.05780 0.05007 -0.0701 0.0502 1.0000
14.000 1.3904 0.06093 0.05320 -0.0695 0.0409 1.0000
14.250 1.3876 0.06423 0.05653 -0.0690 0.0327 1.0000
14.500 1.3850 0.06761 0.05995 -0.0687 0.0263 1.0000
14.750 1.3828 0.07106 0.06344 -0.0685 0.0219 1.0000
15.000 1.3799 0.07465 0.06710 -0.0684 0.0189 1.0000
15.250 1.3792 0.07804 0.07059 -0.0685 0.0171 1.0000
15.500 1.3772 0.08167 0.07432 -0.0687 0.0158 1.0000
15.750 1.3748 0.08544 0.07818 -0.0691 0.0150 1.0000
16.000 1.3734 0.08915 0.08203 -0.0695 0.0142 1.0000
16.250 1.3718 0.09292 0.08593 -0.0702 0.0135 1.0000
16.500 1.3694 0.09686 0.09000 -0.0709 0.0130 1.0000
16.750 1.3661 0.10099 0.09425 -0.0719 0.0125 1.0000
17.000 1.3618 0.10536 0.09872 -0.0730 0.0121 1.0000
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Polar data table (+)
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