Ornithopter airfoil. (s1020-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: Ornithopter airfoil. (s1020-il) Reynolds number: 100,000 Max Cl/Cd: 53.41 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s1020-il-100000-n5.txt Download as CSV file: xf-s1020-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2523 0.10671 0.10173 -0.0777 0.9718 0.0298
-10.250 -0.2472 0.10213 0.09715 -0.0807 0.9664 0.0297
-10.000 -0.2461 0.09525 0.09029 -0.0863 0.9625 0.0298
-9.750 -0.2469 0.09020 0.08526 -0.0891 0.9553 0.0297
-9.500 -0.2425 0.08467 0.07973 -0.0935 0.9509 0.0295
-9.250 -0.2500 0.07802 0.07310 -0.0976 0.9428 0.0294
-9.000 -0.2572 0.06970 0.06474 -0.1056 0.9370 0.0289
-8.750 -0.2791 0.06295 0.05791 -0.1113 0.9254 0.0286
-8.500 -0.2988 0.05796 0.05278 -0.1153 0.9133 0.0281
-8.250 -0.3093 0.05281 0.04733 -0.1187 0.9034 0.0280
-8.000 -0.3085 0.04808 0.04218 -0.1214 0.8962 0.0281
-7.750 -0.3058 0.04458 0.03829 -0.1217 0.8880 0.0281
-7.500 -0.2918 0.04099 0.03424 -0.1230 0.8825 0.0280
-7.250 -0.2676 0.03760 0.03032 -0.1252 0.8797 0.0282
-7.000 -0.2568 0.03564 0.02801 -0.1237 0.8714 0.0283
-6.750 -0.2305 0.03328 0.02525 -0.1247 0.8677 0.0287
-6.500 -0.1992 0.03119 0.02277 -0.1261 0.8653 0.0292
-6.250 -0.1796 0.02992 0.02125 -0.1252 0.8590 0.0297
-6.000 -0.1544 0.02855 0.01976 -0.1252 0.8543 0.0303
-5.750 -0.1226 0.02736 0.01852 -0.1266 0.8515 0.0321
-5.500 -0.0874 0.02624 0.01726 -0.1284 0.8494 0.0346
-5.250 -0.0724 0.02571 0.01661 -0.1263 0.8413 0.0362
-5.000 -0.0422 0.02465 0.01549 -0.1272 0.8377 0.0382
-4.750 -0.0069 0.02368 0.01444 -0.1290 0.8352 0.0411
-4.500 0.0173 0.02310 0.01372 -0.1287 0.8296 0.0449
-4.250 0.0432 0.02241 0.01301 -0.1288 0.8240 0.0525
-4.000 0.0787 0.02138 0.01206 -0.1307 0.8211 0.0807
-3.750 0.1171 0.02024 0.01126 -0.1336 0.8189 0.1600
-3.500 0.1325 0.01964 0.01123 -0.1323 0.8108 0.2752
-3.250 0.1646 0.01916 0.01118 -0.1334 0.8069 0.3985
-3.000 0.2021 0.01895 0.01092 -0.1352 0.8042 0.4534
-2.750 0.2218 0.01907 0.01102 -0.1336 0.7971 0.4843
-2.500 0.2516 0.01901 0.01090 -0.1339 0.7922 0.5126
-2.250 0.2876 0.01885 0.01065 -0.1352 0.7891 0.5388
-2.000 0.3090 0.01896 0.01072 -0.1340 0.7824 0.5584
-1.750 0.3372 0.01892 0.01061 -0.1339 0.7771 0.5779
-1.500 0.3728 0.01876 0.01035 -0.1353 0.7737 0.5973
-1.250 0.3933 0.01888 0.01045 -0.1339 0.7668 0.6125
-1.000 0.4215 0.01884 0.01035 -0.1339 0.7614 0.6279
-0.750 0.4571 0.01867 0.01011 -0.1352 0.7580 0.6436
-0.500 0.4751 0.01884 0.01027 -0.1334 0.7505 0.6571
-0.250 0.5045 0.01878 0.01017 -0.1336 0.7454 0.6721
0.000 0.5405 0.01860 0.00993 -0.1350 0.7420 0.6877
0.250 0.5550 0.01884 0.01020 -0.1326 0.7336 0.7020
0.500 0.5862 0.01875 0.01007 -0.1331 0.7290 0.7182
0.750 0.6140 0.01874 0.01005 -0.1331 0.7238 0.7347
1.000 0.6333 0.01887 0.01021 -0.1315 0.7166 0.7518
1.250 0.6660 0.01873 0.01005 -0.1322 0.7123 0.7707
1.500 0.6829 0.01892 0.01028 -0.1302 0.7050 0.7912
1.750 0.7075 0.01887 0.01027 -0.1294 0.6993 0.8135
2.000 0.7393 0.01869 0.01009 -0.1298 0.6953 0.8403
2.250 0.7480 0.01891 0.01042 -0.1262 0.6868 0.8764
2.500 0.7836 0.01870 0.01024 -0.1275 0.6821 0.9336
2.750 0.8096 0.01889 0.01041 -0.1277 0.6749 1.0000
3.000 0.8391 0.01903 0.01049 -0.1284 0.6688 1.0000
3.250 0.8731 0.01908 0.01048 -0.1297 0.6637 1.0000
3.500 0.8910 0.01945 0.01085 -0.1283 0.6558 1.0000
3.750 0.9268 0.01945 0.01078 -0.1299 0.6508 1.0000
4.000 0.9429 0.01985 0.01121 -0.1281 0.6427 1.0000
4.250 0.9741 0.01994 0.01128 -0.1289 0.6369 1.0000
4.500 0.9952 0.02024 0.01159 -0.1279 0.6297 1.0000
4.750 1.0204 0.02045 0.01180 -0.1277 0.6229 1.0000
5.000 1.0473 0.02063 0.01200 -0.1277 0.6165 1.0000
5.250 1.0661 0.02096 0.01236 -0.1262 0.6087 1.0000
5.500 1.0977 0.02105 0.01245 -0.1271 0.6027 1.0000
5.750 1.1110 0.02151 0.01297 -0.1247 0.5942 1.0000
6.000 1.1439 0.02156 0.01303 -0.1257 0.5880 1.0000
6.250 1.1547 0.02207 0.01363 -0.1229 0.5790 1.0000
6.500 1.1841 0.02218 0.01375 -0.1233 0.5720 1.0000
6.750 1.1970 0.02267 0.01433 -0.1209 0.5630 1.0000
7.000 1.2206 0.02291 0.01461 -0.1203 0.5552 1.0000
7.250 1.2380 0.02330 0.01507 -0.1187 0.5463 1.0000
7.500 1.2553 0.02371 0.01554 -0.1171 0.5375 1.0000
7.750 1.2786 0.02394 0.01584 -0.1165 0.5289 1.0000
8.000 1.2893 0.02454 0.01654 -0.1139 0.5190 1.0000
8.250 1.3110 0.02483 0.01687 -0.1130 0.5100 1.0000
8.500 1.3241 0.02536 0.01749 -0.1108 0.4997 1.0000
8.750 1.3357 0.02598 0.01820 -0.1085 0.4891 1.0000
9.000 1.3520 0.02643 0.01872 -0.1069 0.4784 1.0000
9.250 1.3664 0.02695 0.01930 -0.1050 0.4672 1.0000
9.500 1.3732 0.02779 0.02025 -0.1022 0.4551 1.0000
9.750 1.3822 0.02858 0.02113 -0.0998 0.4427 1.0000
10.000 1.3913 0.02940 0.02202 -0.0974 0.4298 1.0000
10.250 1.3990 0.03030 0.02300 -0.0950 0.4161 1.0000
10.500 1.4051 0.03133 0.02409 -0.0925 0.4016 1.0000
10.750 1.4096 0.03252 0.02534 -0.0899 0.3864 1.0000
11.000 1.4126 0.03385 0.02672 -0.0874 0.3704 1.0000
11.250 1.4148 0.03532 0.02823 -0.0849 0.3537 1.0000
11.500 1.4160 0.03693 0.02987 -0.0825 0.3362 1.0000
11.750 1.4165 0.03869 0.03163 -0.0802 0.3184 1.0000
12.000 1.4150 0.04068 0.03362 -0.0780 0.2994 1.0000
12.250 1.4120 0.04294 0.03588 -0.0759 0.2796 1.0000
12.500 1.4077 0.04542 0.03831 -0.0739 0.2597 1.0000
12.750 1.4016 0.04820 0.04104 -0.0721 0.2390 1.0000
13.000 1.3943 0.05127 0.04405 -0.0705 0.2175 1.0000
13.250 1.3856 0.05463 0.04733 -0.0691 0.1971 1.0000
13.500 1.3780 0.05809 0.05075 -0.0681 0.1766 1.0000
14.000 1.3596 0.06585 0.05835 -0.0667 0.1369 1.0000
14.250 1.3513 0.06985 0.06231 -0.0664 0.1197 1.0000
14.500 1.3442 0.07386 0.06630 -0.0664 0.1050 1.0000
14.750 1.3379 0.07789 0.07036 -0.0664 0.0921 1.0000
15.000 1.3317 0.08200 0.07449 -0.0667 0.0803 1.0000
15.250 1.3258 0.08619 0.07871 -0.0671 0.0699 1.0000
15.500 1.3195 0.09054 0.08311 -0.0676 0.0607 1.0000
15.750 1.3125 0.09508 0.08769 -0.0684 0.0527 1.0000
16.000 1.3039 0.09995 0.09258 -0.0694 0.0461 1.0000
16.250 1.2975 0.10459 0.09732 -0.0705 0.0405 1.0000
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Polar data table (+)
Polar graphs
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