Ornithopter airfoil. (s1020-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: Ornithopter airfoil. (s1020-il) Reynolds number: 500,000 Max Cl/Cd: 111.15 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1020-il-500000-n5.txt Download as CSV file: xf-s1020-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.1776 0.09846 0.09591 -0.1007 0.9705 0.0111
-11.250 -0.3312 0.05307 0.05025 -0.1268 0.9519 0.0099
-10.750 -0.3691 0.03692 0.03352 -0.1445 0.9288 0.0098
-10.500 -0.3667 0.03178 0.02803 -0.1522 0.9186 0.0098
-10.250 -0.3487 0.02826 0.02414 -0.1577 0.9104 0.0100
-10.000 -0.3292 0.02585 0.02142 -0.1604 0.9015 0.0101
-9.500 -0.2857 0.02231 0.01733 -0.1633 0.8841 0.0104
-9.250 -0.2633 0.02101 0.01580 -0.1639 0.8760 0.0106
-9.000 -0.2422 0.01992 0.01450 -0.1639 0.8673 0.0108
-8.750 -0.2203 0.01900 0.01340 -0.1638 0.8596 0.0110
-8.500 -0.1983 0.01815 0.01238 -0.1635 0.8516 0.0111
-8.250 -0.1760 0.01741 0.01150 -0.1632 0.8446 0.0113
-8.000 -0.1532 0.01679 0.01074 -0.1628 0.8373 0.0114
-7.750 -0.1297 0.01621 0.01003 -0.1626 0.8308 0.0115
-7.500 -0.1085 0.01541 0.00914 -0.1619 0.8237 0.0117
-7.250 -0.0857 0.01469 0.00832 -0.1616 0.8176 0.0120
-7.000 -0.0631 0.01416 0.00773 -0.1611 0.8110 0.0123
-6.750 -0.0389 0.01369 0.00719 -0.1608 0.8048 0.0127
-6.500 -0.0144 0.01331 0.00676 -0.1605 0.7990 0.0132
-6.250 0.0100 0.01292 0.00630 -0.1602 0.7928 0.0136
-6.000 0.0356 0.01256 0.00584 -0.1601 0.7873 0.0140
-5.750 0.0602 0.01220 0.00542 -0.1597 0.7814 0.0144
-5.500 0.0857 0.01189 0.00503 -0.1595 0.7755 0.0148
-5.250 0.1118 0.01163 0.00469 -0.1594 0.7702 0.0151
-5.000 0.1371 0.01127 0.00428 -0.1592 0.7643 0.0159
-4.750 0.1633 0.01104 0.00398 -0.1590 0.7587 0.0168
-4.500 0.1897 0.01084 0.00373 -0.1589 0.7534 0.0177
-4.250 0.2159 0.01067 0.00350 -0.1587 0.7475 0.0191
-4.000 0.2425 0.01047 0.00327 -0.1586 0.7421 0.0229
-3.750 0.2685 0.01017 0.00305 -0.1585 0.7365 0.0451
-3.500 0.2945 0.00987 0.00286 -0.1585 0.7306 0.0807
-3.000 0.3470 0.00930 0.00256 -0.1585 0.7194 0.1770
-2.750 0.3731 0.00900 0.00245 -0.1585 0.7135 0.2427
-2.500 0.3994 0.00872 0.00237 -0.1586 0.7080 0.3150
-2.250 0.4258 0.00856 0.00234 -0.1585 0.7020 0.3710
-2.000 0.4523 0.00848 0.00234 -0.1584 0.6962 0.4197
-1.750 0.4791 0.00844 0.00234 -0.1583 0.6904 0.4469
-1.500 0.5056 0.00844 0.00233 -0.1581 0.6842 0.4623
-1.250 0.5322 0.00846 0.00233 -0.1579 0.6785 0.4771
-1.000 0.5588 0.00847 0.00234 -0.1577 0.6722 0.4901
-0.750 0.5850 0.00851 0.00234 -0.1574 0.6661 0.5024
-0.500 0.6115 0.00853 0.00236 -0.1572 0.6601 0.5146
-0.250 0.6376 0.00856 0.00238 -0.1570 0.6538 0.5258
0.000 0.6636 0.00861 0.00241 -0.1567 0.6478 0.5363
0.250 0.6896 0.00864 0.00245 -0.1564 0.6411 0.5469
0.500 0.7151 0.00871 0.00249 -0.1560 0.6350 0.5571
0.750 0.7411 0.00875 0.00254 -0.1557 0.6284 0.5682
1.000 0.7662 0.00881 0.00260 -0.1552 0.6217 0.5796
1.250 0.7917 0.00887 0.00267 -0.1548 0.6155 0.5909
1.500 0.8167 0.00893 0.00274 -0.1543 0.6084 0.6026
1.750 0.8414 0.00901 0.00282 -0.1538 0.6020 0.6151
2.000 0.8662 0.00908 0.00292 -0.1533 0.5948 0.6276
2.250 0.8901 0.00917 0.00301 -0.1526 0.5881 0.6403
2.500 0.9144 0.00924 0.00311 -0.1520 0.5809 0.6538
2.750 0.9370 0.00934 0.00323 -0.1510 0.5739 0.6675
3.000 0.9606 0.00942 0.00334 -0.1502 0.5668 0.6822
3.250 0.9827 0.00952 0.00347 -0.1492 0.5597 0.6978
3.500 1.0056 0.00961 0.00360 -0.1483 0.5527 0.7142
3.750 1.0272 0.00973 0.00376 -0.1471 0.5451 0.7312
4.000 1.0493 0.00984 0.00392 -0.1461 0.5379 0.7504
4.250 1.0703 0.00998 0.00410 -0.1448 0.5299 0.7714
4.500 1.0915 0.01010 0.00429 -0.1436 0.5222 0.7938
4.750 1.1107 0.01024 0.00448 -0.1420 0.5139 0.8203
5.000 1.1296 0.01033 0.00467 -0.1402 0.5061 0.8552
5.250 1.1437 0.01038 0.00484 -0.1374 0.4982 0.9239
5.500 1.1693 0.01052 0.00501 -0.1372 0.4895 1.0000
5.750 1.1894 0.01078 0.00524 -0.1360 0.4812 1.0000
6.000 1.2109 0.01100 0.00546 -0.1349 0.4723 1.0000
6.250 1.2306 0.01127 0.00572 -0.1336 0.4638 1.0000
6.500 1.2500 0.01155 0.00600 -0.1323 0.4535 1.0000
6.750 1.2694 0.01185 0.00628 -0.1309 0.4430 1.0000
7.000 1.2874 0.01218 0.00660 -0.1294 0.4330 1.0000
7.250 1.3043 0.01256 0.00695 -0.1276 0.4212 1.0000
7.500 1.3214 0.01295 0.00733 -0.1259 0.4081 1.0000
8.000 1.3465 0.01406 0.00831 -0.1212 0.3700 1.0000
8.250 1.3558 0.01479 0.00894 -0.1184 0.3469 1.0000
8.500 1.3646 0.01559 0.00965 -0.1156 0.3231 1.0000
8.750 1.3704 0.01656 0.01049 -0.1125 0.2964 1.0000
9.000 1.3750 0.01766 0.01145 -0.1093 0.2686 1.0000
9.250 1.3786 0.01888 0.01252 -0.1062 0.2404 1.0000
9.500 1.3821 0.02016 0.01367 -0.1032 0.2138 1.0000
9.750 1.3857 0.02151 0.01490 -0.1004 0.1882 1.0000
10.000 1.3904 0.02285 0.01615 -0.0978 0.1676 1.0000
10.250 1.3945 0.02428 0.01749 -0.0953 0.1464 1.0000
10.500 1.3980 0.02582 0.01894 -0.0929 0.1272 1.0000
10.750 1.4017 0.02740 0.02045 -0.0907 0.1090 1.0000
11.000 1.4037 0.02917 0.02213 -0.0884 0.0912 1.0000
11.250 1.4071 0.03091 0.02382 -0.0864 0.0766 1.0000
11.500 1.4089 0.03284 0.02568 -0.0844 0.0612 1.0000
11.750 1.4108 0.03484 0.02764 -0.0826 0.0485 1.0000
12.000 1.4122 0.03695 0.02972 -0.0808 0.0374 1.0000
12.250 1.4154 0.03899 0.03174 -0.0794 0.0291 1.0000
12.500 1.4171 0.04122 0.03396 -0.0779 0.0207 1.0000
12.750 1.4174 0.04366 0.03639 -0.0766 0.0136 1.0000
13.000 1.4200 0.04596 0.03872 -0.0754 0.0106 1.0000
13.250 1.4238 0.04821 0.04103 -0.0745 0.0092 1.0000
13.500 1.4294 0.05033 0.04322 -0.0738 0.0086 1.0000
13.750 1.4343 0.05256 0.04554 -0.0730 0.0081 1.0000
14.000 1.4390 0.05487 0.04792 -0.0724 0.0078 1.0000
14.250 1.4425 0.05738 0.05052 -0.0719 0.0074 1.0000
14.500 1.4452 0.06003 0.05325 -0.0715 0.0071 1.0000
14.750 1.4472 0.06283 0.05613 -0.0711 0.0069 1.0000
15.000 1.4494 0.06565 0.05904 -0.0708 0.0066 1.0000
15.250 1.4519 0.06849 0.06198 -0.0707 0.0065 1.0000
15.500 1.4538 0.07147 0.06506 -0.0707 0.0064 1.0000
15.750 1.4553 0.07456 0.06826 -0.0707 0.0063 1.0000
16.000 1.4558 0.07784 0.07164 -0.0709 0.0062 1.0000
16.250 1.4560 0.08118 0.07508 -0.0712 0.0060 1.0000
16.500 1.4553 0.08474 0.07874 -0.0716 0.0060 1.0000
16.750 1.4542 0.08842 0.08252 -0.0721 0.0058 1.0000
17.000 1.4526 0.09222 0.08643 -0.0728 0.0057 1.0000
17.250 1.4506 0.09613 0.09044 -0.0736 0.0056 1.0000
17.500 1.4482 0.10013 0.09454 -0.0745 0.0055 1.0000
17.750 1.4455 0.10424 0.09875 -0.0755 0.0054 1.0000
18.000 1.4418 0.10855 0.10317 -0.0768 0.0053 1.0000
18.250 1.4380 0.11293 0.10764 -0.0781 0.0052 1.0000
18.500 1.4335 0.11745 0.11227 -0.0797 0.0052 1.0000
18.750 1.4283 0.12212 0.11705 -0.0814 0.0051 1.0000
19.000 1.4224 0.12695 0.12197 -0.0832 0.0050 1.0000
19.250 1.4171 0.13169 0.12681 -0.0852 0.0049 1.0000
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