Ornithopter airfoil. (s1020-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Ornithopter airfoil. (s1020-il) Reynolds number: 1,000,000 Max Cl/Cd: 127.17 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1020-il-1000000-n5.txt Download as CSV file: xf-s1020-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4473 0.05323 0.05080 -0.1302 0.9760 0.0072
-12.750 -0.4654 0.04378 0.04111 -0.1408 0.9738 0.0071
-12.250 -0.4891 0.03534 0.03241 -0.1454 0.9532 0.0073
-12.000 -0.4893 0.03117 0.02805 -0.1499 0.9428 0.0073
-11.750 -0.4708 0.02752 0.02418 -0.1570 0.9356 0.0073
-11.500 -0.4428 0.02441 0.02083 -0.1646 0.9262 0.0074
-11.250 -0.4165 0.02229 0.01846 -0.1692 0.9140 0.0075
-11.000 -0.3955 0.02073 0.01668 -0.1710 0.8997 0.0075
-10.750 -0.3773 0.01976 0.01552 -0.1711 0.8859 0.0077
-10.500 -0.3616 0.01884 0.01443 -0.1704 0.8736 0.0078
-10.250 -0.3451 0.01805 0.01347 -0.1695 0.8624 0.0080
-10.000 -0.3277 0.01736 0.01266 -0.1686 0.8522 0.0081
-9.750 -0.3090 0.01672 0.01189 -0.1677 0.8435 0.0082
-9.500 -0.2904 0.01606 0.01109 -0.1668 0.8348 0.0082
-9.250 -0.2694 0.01556 0.01050 -0.1662 0.8274 0.0083
-9.000 -0.2484 0.01507 0.00989 -0.1655 0.8198 0.0084
-8.750 -0.2261 0.01463 0.00937 -0.1650 0.8132 0.0085
-8.500 -0.2041 0.01416 0.00880 -0.1644 0.8062 0.0085
-8.250 -0.1844 0.01335 0.00788 -0.1636 0.7999 0.0087
-8.000 -0.1622 0.01280 0.00725 -0.1630 0.7935 0.0089
-7.750 -0.1393 0.01237 0.00674 -0.1625 0.7874 0.0091
-7.500 -0.1150 0.01197 0.00629 -0.1622 0.7816 0.0092
-7.250 -0.0907 0.01164 0.00590 -0.1618 0.7754 0.0094
-7.000 -0.0659 0.01134 0.00553 -0.1615 0.7700 0.0096
-6.750 -0.0408 0.01102 0.00516 -0.1613 0.7642 0.0098
-6.500 -0.0158 0.01075 0.00483 -0.1610 0.7584 0.0100
-6.250 0.0100 0.01048 0.00451 -0.1608 0.7532 0.0103
-6.000 0.0358 0.01025 0.00423 -0.1606 0.7473 0.0106
-5.500 0.0880 0.00985 0.00373 -0.1603 0.7366 0.0113
-5.250 0.1141 0.00968 0.00351 -0.1601 0.7306 0.0115
-5.000 0.1399 0.00943 0.00320 -0.1599 0.7253 0.0120
-4.750 0.1666 0.00923 0.00296 -0.1598 0.7196 0.0126
-4.500 0.1929 0.00908 0.00277 -0.1596 0.7138 0.0131
-4.250 0.2195 0.00895 0.00261 -0.1595 0.7085 0.0138
-4.000 0.2464 0.00884 0.00245 -0.1594 0.7026 0.0145
-3.750 0.2726 0.00875 0.00232 -0.1592 0.6967 0.0154
-3.500 0.2996 0.00862 0.00218 -0.1592 0.6913 0.0182
-3.250 0.3259 0.00838 0.00203 -0.1591 0.6851 0.0445
-3.000 0.3520 0.00818 0.00191 -0.1589 0.6795 0.0757
-2.750 0.3789 0.00795 0.00180 -0.1590 0.6736 0.1182
-2.500 0.4051 0.00780 0.00173 -0.1589 0.6674 0.1540
-2.250 0.4317 0.00759 0.00165 -0.1589 0.6618 0.2052
-2.000 0.4583 0.00738 0.00160 -0.1590 0.6556 0.2644
-1.750 0.4842 0.00722 0.00157 -0.1588 0.6494 0.3246
-1.500 0.5113 0.00706 0.00157 -0.1589 0.6435 0.3829
-1.250 0.5376 0.00702 0.00159 -0.1587 0.6371 0.4200
-1.000 0.5642 0.00703 0.00160 -0.1586 0.6312 0.4364
-0.750 0.5908 0.00704 0.00162 -0.1584 0.6245 0.4509
-0.500 0.6168 0.00708 0.00164 -0.1581 0.6184 0.4632
-0.250 0.6436 0.00710 0.00167 -0.1580 0.6119 0.4740
0.000 0.6692 0.00716 0.00170 -0.1576 0.6051 0.4852
0.250 0.6957 0.00719 0.00174 -0.1574 0.5990 0.4964
0.500 0.7213 0.00724 0.00178 -0.1570 0.5919 0.5058
0.750 0.7470 0.00730 0.00183 -0.1567 0.5854 0.5155
1.000 0.7725 0.00735 0.00188 -0.1563 0.5784 0.5243
1.250 0.7969 0.00743 0.00194 -0.1557 0.5715 0.5343
1.500 0.8219 0.00748 0.00200 -0.1552 0.5644 0.5448
1.750 0.8456 0.00756 0.00207 -0.1544 0.5574 0.5547
2.000 0.8707 0.00762 0.00215 -0.1540 0.5505 0.5658
2.500 0.9188 0.00778 0.00232 -0.1527 0.5365 0.5883
3.000 0.9665 0.00798 0.00254 -0.1513 0.5219 0.6120
3.250 0.9897 0.00810 0.00266 -0.1505 0.5139 0.6246
3.500 1.0136 0.00821 0.00279 -0.1498 0.5062 0.6374
3.750 1.0361 0.00836 0.00294 -0.1489 0.4975 0.6504
4.000 1.0599 0.00847 0.00308 -0.1482 0.4895 0.6650
4.500 1.1050 0.00875 0.00340 -0.1464 0.4729 0.6952
4.750 1.1269 0.00891 0.00358 -0.1454 0.4651 0.7118
5.000 1.1496 0.00904 0.00375 -0.1446 0.4564 0.7302
5.250 1.1712 0.00921 0.00395 -0.1435 0.4479 0.7497
5.500 1.1923 0.00938 0.00416 -0.1424 0.4381 0.7708
5.750 1.2129 0.00955 0.00438 -0.1411 0.4279 0.7952
6.000 1.2319 0.00975 0.00462 -0.1396 0.4175 0.8250
6.250 1.2486 0.00995 0.00489 -0.1375 0.4051 0.8669
6.500 1.2652 0.01006 0.00512 -0.1355 0.3899 1.0000
6.750 1.2830 0.01043 0.00542 -0.1338 0.3732 1.0000
7.000 1.2988 0.01087 0.00578 -0.1319 0.3530 1.0000
7.250 1.3118 0.01143 0.00622 -0.1295 0.3287 1.0000
7.500 1.3233 0.01207 0.00673 -0.1269 0.3021 1.0000
7.750 1.3349 0.01272 0.00726 -0.1243 0.2774 1.0000
8.000 1.3414 0.01361 0.00796 -0.1210 0.2449 1.0000
8.250 1.3464 0.01460 0.00877 -0.1176 0.2126 1.0000
8.500 1.3538 0.01551 0.00955 -0.1146 0.1862 1.0000
8.750 1.3615 0.01644 0.01037 -0.1118 0.1632 1.0000
9.000 1.3677 0.01749 0.01129 -0.1089 0.1405 1.0000
9.250 1.3752 0.01851 0.01222 -0.1063 0.1206 1.0000
9.500 1.3822 0.01959 0.01321 -0.1038 0.1034 1.0000
9.750 1.3890 0.02073 0.01427 -0.1013 0.0862 1.0000
10.000 1.3958 0.02192 0.01540 -0.0989 0.0715 1.0000
10.250 1.4016 0.02321 0.01663 -0.0966 0.0580 1.0000
10.500 1.4063 0.02463 0.01799 -0.0942 0.0441 1.0000
10.750 1.4092 0.02624 0.01952 -0.0918 0.0308 1.0000
11.000 1.4146 0.02773 0.02099 -0.0897 0.0215 1.0000
11.500 1.4238 0.03101 0.02424 -0.0858 0.0081 1.0000
11.750 1.4328 0.03239 0.02566 -0.0845 0.0072 1.0000
12.000 1.4422 0.03378 0.02708 -0.0832 0.0065 1.0000
12.250 1.4521 0.03514 0.02849 -0.0821 0.0062 1.0000
12.500 1.4609 0.03664 0.03004 -0.0809 0.0059 1.0000
12.750 1.4688 0.03827 0.03172 -0.0798 0.0056 1.0000
13.000 1.4764 0.03995 0.03345 -0.0787 0.0053 1.0000
13.250 1.4831 0.04176 0.03532 -0.0776 0.0051 1.0000
13.500 1.4892 0.04367 0.03730 -0.0766 0.0049 1.0000
13.750 1.4957 0.04559 0.03928 -0.0757 0.0048 1.0000
14.000 1.5025 0.04753 0.04128 -0.0750 0.0047 1.0000
14.250 1.5086 0.04959 0.04340 -0.0743 0.0046 1.0000
14.500 1.5145 0.05168 0.04556 -0.0736 0.0045 1.0000
14.750 1.5196 0.05393 0.04787 -0.0730 0.0044 1.0000
15.000 1.5238 0.05632 0.05033 -0.0725 0.0043 1.0000
15.250 1.5283 0.05873 0.05281 -0.0721 0.0042 1.0000
15.500 1.5325 0.06122 0.05537 -0.0718 0.0041 1.0000
15.750 1.5353 0.06393 0.05816 -0.0715 0.0040 1.0000
16.000 1.5380 0.06669 0.06099 -0.0714 0.0039 1.0000
16.250 1.5400 0.06959 0.06397 -0.0713 0.0038 1.0000
16.500 1.5413 0.07266 0.06712 -0.0714 0.0038 1.0000
16.750 1.5416 0.07590 0.07044 -0.0715 0.0037 1.0000
17.000 1.5415 0.07927 0.07389 -0.0718 0.0036 1.0000
17.250 1.5408 0.08276 0.07746 -0.0722 0.0036 1.0000
17.500 1.5384 0.08656 0.08136 -0.0727 0.0035 1.0000
17.750 1.5367 0.09032 0.08521 -0.0734 0.0035 1.0000
18.000 1.5310 0.09475 0.08974 -0.0742 0.0034 1.0000
18.250 1.5268 0.09902 0.09410 -0.0752 0.0033 1.0000
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