Ornithopter airfoil. (s1020-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: Ornithopter airfoil. (s1020-il) Reynolds number: 1,000,000 Max Cl/Cd: 146.82 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s1020-il-1000000.txt Download as CSV file: xf-s1020-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.1683 0.11072 0.10894 -0.0961 0.9853 0.0150
-12.000 -0.1593 0.10562 0.10383 -0.1002 0.9849 0.0151
-11.750 -0.1697 0.09934 0.09758 -0.1020 0.9807 0.0155
-11.500 -0.1616 0.09511 0.09334 -0.1053 0.9787 0.0156
-11.250 -0.1488 0.09202 0.09026 -0.1084 0.9773 0.0158
-11.000 -0.1374 0.08810 0.08633 -0.1122 0.9761 0.0160
-10.750 -0.1274 0.08354 0.08177 -0.1167 0.9750 0.0163
-10.500 -0.1173 0.07866 0.07689 -0.1217 0.9741 0.0168
-10.250 -0.1186 0.03778 0.03600 -0.1375 0.9464 0.0184
-10.000 -0.1443 0.02688 0.02489 -0.1510 0.9385 0.0181
-9.750 -0.1519 0.01977 0.01742 -0.1653 0.9258 0.0183
-9.500 -0.1490 0.01951 0.01679 -0.1690 0.9051 0.0191
-9.250 -0.2177 0.02333 0.01970 -0.1728 0.9013 0.0140
-9.000 -0.2045 0.02093 0.01697 -0.1725 0.8890 0.0137
-8.750 -0.1940 0.01785 0.01338 -0.1711 0.8776 0.0128
-8.500 -0.1759 0.01649 0.01180 -0.1701 0.8680 0.0126
-8.250 -0.1548 0.01557 0.01074 -0.1695 0.8599 0.0127
-8.000 -0.1330 0.01486 0.00991 -0.1689 0.8520 0.0129
-7.750 -0.1107 0.01419 0.00914 -0.1683 0.8448 0.0131
-7.500 -0.0881 0.01357 0.00843 -0.1677 0.8375 0.0134
-7.250 -0.0649 0.01301 0.00778 -0.1672 0.8310 0.0136
-7.000 -0.0415 0.01252 0.00722 -0.1666 0.8242 0.0139
-6.750 -0.0176 0.01201 0.00661 -0.1662 0.8179 0.0140
-6.500 0.0062 0.01158 0.00613 -0.1657 0.8118 0.0143
-6.250 0.0307 0.01117 0.00564 -0.1653 0.8057 0.0145
-6.000 0.0556 0.01081 0.00521 -0.1650 0.8000 0.0147
-5.750 0.0806 0.01047 0.00482 -0.1647 0.7940 0.0149
-5.500 0.1065 0.01022 0.00448 -0.1645 0.7884 0.0151
-5.250 0.1307 0.00964 0.00384 -0.1641 0.7828 0.0159
-5.000 0.1566 0.00934 0.00348 -0.1639 0.7770 0.0168
-4.750 0.1831 0.00914 0.00321 -0.1638 0.7716 0.0176
-4.500 0.2095 0.00893 0.00297 -0.1636 0.7661 0.0184
-4.250 0.2361 0.00878 0.00277 -0.1635 0.7605 0.0192
-4.000 0.2629 0.00860 0.00253 -0.1633 0.7552 0.0212
-3.750 0.2895 0.00840 0.00235 -0.1632 0.7495 0.0271
-3.500 0.3151 0.00793 0.00212 -0.1632 0.7440 0.0947
-3.250 0.3412 0.00751 0.00196 -0.1633 0.7386 0.1748
-3.000 0.3674 0.00717 0.00185 -0.1633 0.7328 0.2500
-2.750 0.3938 0.00694 0.00177 -0.1633 0.7272 0.3153
-2.500 0.4208 0.00678 0.00173 -0.1633 0.7218 0.3630
-2.250 0.4476 0.00669 0.00172 -0.1633 0.7159 0.4039
-2.000 0.4745 0.00667 0.00171 -0.1632 0.7103 0.4314
-1.750 0.5017 0.00663 0.00171 -0.1631 0.7044 0.4550
-1.500 0.5284 0.00662 0.00172 -0.1629 0.6985 0.4765
-1.250 0.5553 0.00663 0.00173 -0.1628 0.6929 0.4934
-1.000 0.5822 0.00664 0.00174 -0.1627 0.6867 0.5052
-0.750 0.6085 0.00669 0.00175 -0.1624 0.6807 0.5169
-0.500 0.6356 0.00668 0.00177 -0.1624 0.6747 0.5278
-0.250 0.6619 0.00672 0.00178 -0.1621 0.6683 0.5384
0.000 0.6883 0.00676 0.00181 -0.1619 0.6623 0.5498
0.250 0.7147 0.00678 0.00185 -0.1617 0.6558 0.5612
0.500 0.7403 0.00684 0.00189 -0.1613 0.6493 0.5720
1.000 0.7922 0.00692 0.00198 -0.1607 0.6361 0.5952
1.250 0.8182 0.00695 0.00203 -0.1604 0.6295 0.6076
1.500 0.8434 0.00701 0.00209 -0.1599 0.6224 0.6206
1.750 0.8688 0.00707 0.00216 -0.1595 0.6158 0.6343
2.000 0.8940 0.00713 0.00223 -0.1591 0.6086 0.6487
2.500 0.9430 0.00725 0.00240 -0.1579 0.5946 0.6795
3.000 0.9901 0.00738 0.00258 -0.1563 0.5801 0.7125
3.250 1.0123 0.00748 0.00269 -0.1553 0.5727 0.7305
3.500 1.0361 0.00753 0.00281 -0.1545 0.5650 0.7497
3.750 1.0577 0.00765 0.00294 -0.1534 0.5572 0.7703
4.000 1.0810 0.00772 0.00307 -0.1525 0.5493 0.7930
4.250 1.1020 0.00783 0.00322 -0.1512 0.5418 0.8189
4.500 1.1241 0.00789 0.00337 -0.1501 0.5341 0.8489
4.750 1.1417 0.00796 0.00353 -0.1480 0.5267 0.8932
5.000 1.1643 0.00793 0.00362 -0.1470 0.5190 1.0000
5.250 1.1860 0.00813 0.00379 -0.1460 0.5110 1.0000
5.500 1.2092 0.00828 0.00394 -0.1453 0.5025 1.0000
5.750 1.2309 0.00849 0.00411 -0.1442 0.4940 1.0000
6.000 1.2529 0.00868 0.00429 -0.1433 0.4850 1.0000
6.250 1.2743 0.00889 0.00448 -0.1422 0.4749 1.0000
6.500 1.2937 0.00915 0.00471 -0.1408 0.4636 1.0000
6.750 1.3128 0.00943 0.00494 -0.1394 0.4518 1.0000
7.000 1.3328 0.00969 0.00518 -0.1381 0.4392 1.0000
7.250 1.3505 0.01003 0.00547 -0.1364 0.4236 1.0000
7.500 1.3660 0.01044 0.00581 -0.1343 0.4062 1.0000
7.750 1.3821 0.01085 0.00616 -0.1324 0.3883 1.0000
8.000 1.3946 0.01141 0.00660 -0.1299 0.3629 1.0000
8.250 1.4074 0.01196 0.00707 -0.1275 0.3421 1.0000
8.500 1.4198 0.01257 0.00758 -0.1251 0.3201 1.0000
8.750 1.4261 0.01343 0.00829 -0.1218 0.2895 1.0000
9.000 1.4350 0.01423 0.00897 -0.1190 0.2661 1.0000
9.250 1.4427 0.01512 0.00974 -0.1161 0.2423 1.0000
9.500 1.4497 0.01606 0.01058 -0.1132 0.2184 1.0000
9.750 1.4550 0.01713 0.01153 -0.1101 0.1950 1.0000
10.000 1.4575 0.01840 0.01265 -0.1069 0.1685 1.0000
10.500 1.4608 0.02123 0.01521 -0.1005 0.1189 1.0000
10.750 1.4617 0.02279 0.01666 -0.0975 0.0965 1.0000
11.000 1.4608 0.02456 0.01829 -0.0945 0.0747 1.0000
11.250 1.4618 0.02629 0.01994 -0.0919 0.0580 1.0000
11.500 1.4582 0.02843 0.02196 -0.0890 0.0385 1.0000
11.750 1.4566 0.03054 0.02399 -0.0865 0.0242 1.0000
12.000 1.4536 0.03286 0.02625 -0.0841 0.0125 1.0000
12.250 1.4601 0.03449 0.02792 -0.0826 0.0106 1.0000
12.500 1.4660 0.03623 0.02969 -0.0812 0.0095 1.0000
12.750 1.4729 0.03794 0.03146 -0.0799 0.0088 1.0000
13.000 1.4804 0.03962 0.03321 -0.0788 0.0084 1.0000
13.250 1.4868 0.04146 0.03512 -0.0777 0.0081 1.0000
13.500 1.4923 0.04342 0.03713 -0.0766 0.0078 1.0000
13.750 1.4968 0.04553 0.03932 -0.0756 0.0075 1.0000
14.000 1.5007 0.04779 0.04164 -0.0747 0.0073 1.0000
14.250 1.5013 0.05043 0.04437 -0.0738 0.0069 1.0000
14.500 1.5004 0.05333 0.04736 -0.0729 0.0068 1.0000
14.750 1.5061 0.05555 0.04965 -0.0724 0.0067 1.0000
15.000 1.5095 0.05809 0.05227 -0.0719 0.0065 1.0000
15.250 1.5118 0.06082 0.05508 -0.0715 0.0064 1.0000
15.500 1.5134 0.06368 0.05803 -0.0712 0.0063 1.0000
15.750 1.5142 0.06672 0.06115 -0.0711 0.0062 1.0000
16.000 1.5143 0.06990 0.06442 -0.0710 0.0061 1.0000
16.250 1.5141 0.07320 0.06781 -0.0711 0.0060 1.0000
16.500 1.5127 0.07673 0.07143 -0.0712 0.0059 1.0000
16.750 1.5112 0.08032 0.07511 -0.0716 0.0058 1.0000
17.000 1.5086 0.08416 0.07904 -0.0720 0.0057 1.0000
17.250 1.5060 0.08806 0.08303 -0.0726 0.0057 1.0000
17.500 1.5026 0.09214 0.08721 -0.0734 0.0056 1.0000
17.750 1.4995 0.09623 0.09139 -0.0743 0.0055 1.0000
18.000 1.4951 0.10058 0.09583 -0.0753 0.0055 1.0000
18.250 1.4908 0.10494 0.10029 -0.0764 0.0054 1.0000
18.500 1.4857 0.10949 0.10494 -0.0778 0.0054 1.0000
18.750 1.4805 0.11412 0.10965 -0.0793 0.0053 1.0000
19.000 1.4748 0.11885 0.11448 -0.0809 0.0052 1.0000
19.250 1.4702 0.12342 0.11914 -0.0826 0.0052 1.0000
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Polar data table (+)
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