DAE-11 AIRFOIL (dae11-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: DAE-11 AIRFOIL (dae11-il) Reynolds number: 500,000 Max Cl/Cd: 132.51 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dae11-il-500000-n5.txt Download as CSV file: xf-dae11-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DAE-11 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.0510 0.08450 0.08070 -0.0754 0.6739 0.0134
-8.250 -0.0607 0.07807 0.07429 -0.0784 0.6725 0.0117
-8.000 -0.0604 0.07417 0.07043 -0.0802 0.6708 0.0119
-7.750 -0.0410 0.07454 0.07081 -0.0800 0.6690 0.0125
-7.500 -0.0362 0.07186 0.06816 -0.0813 0.6673 0.0128
-7.250 -0.0368 0.06858 0.06490 -0.0826 0.6657 0.0126
-7.000 -0.0344 0.06613 0.06247 -0.0838 0.6639 0.0130
-6.750 -0.0293 0.06252 0.05886 -0.0872 0.6622 0.0130
-6.500 -0.0225 0.05796 0.05428 -0.0922 0.6606 0.0129
-6.250 -0.0144 0.05072 0.04699 -0.1008 0.6592 0.0125
-6.000 -0.0155 0.02442 0.01955 -0.1208 0.6580 0.0127
-5.750 0.0071 0.02019 0.01470 -0.1222 0.6565 0.0131
-5.500 0.0330 0.01821 0.01233 -0.1228 0.6547 0.0134
-5.250 0.0599 0.01690 0.01073 -0.1231 0.6528 0.0139
-5.000 0.0874 0.01587 0.00944 -0.1233 0.6510 0.0144
-4.750 0.1152 0.01503 0.00837 -0.1234 0.6494 0.0147
-4.500 0.1428 0.01421 0.00740 -0.1236 0.6477 0.0150
-4.250 0.1707 0.01368 0.00679 -0.1237 0.6461 0.0154
-4.000 0.1989 0.01328 0.00629 -0.1239 0.6444 0.0158
-3.750 0.2272 0.01288 0.00584 -0.1240 0.6428 0.0163
-3.500 0.2557 0.01249 0.00540 -0.1242 0.6410 0.0169
-3.250 0.2841 0.01213 0.00499 -0.1243 0.6390 0.0175
-3.000 0.3127 0.01183 0.00462 -0.1245 0.6369 0.0181
-2.750 0.3411 0.01150 0.00428 -0.1246 0.6350 0.0190
-2.500 0.3697 0.01131 0.00407 -0.1248 0.6332 0.0202
-2.250 0.3983 0.01112 0.00383 -0.1250 0.6314 0.0216
-2.000 0.4269 0.01090 0.00356 -0.1251 0.6296 0.0229
-1.750 0.4556 0.01074 0.00339 -0.1253 0.6277 0.0247
-1.500 0.4844 0.01059 0.00323 -0.1255 0.6257 0.0268
-1.250 0.5131 0.01045 0.00311 -0.1257 0.6234 0.0306
-1.000 0.5418 0.01032 0.00300 -0.1259 0.6211 0.0360
-0.750 0.5705 0.01020 0.00289 -0.1261 0.6188 0.0445
-0.500 0.5991 0.01007 0.00280 -0.1263 0.6167 0.0616
-0.250 0.6276 0.00994 0.00273 -0.1265 0.6146 0.0906
0.000 0.6560 0.00976 0.00271 -0.1267 0.6123 0.1469
0.250 0.6843 0.00953 0.00273 -0.1271 0.6096 0.2324
0.500 0.7124 0.00929 0.00277 -0.1273 0.6067 0.3331
0.750 0.7402 0.00906 0.00281 -0.1275 0.6039 0.4444
1.000 0.7676 0.00884 0.00285 -0.1276 0.6013 0.5530
1.250 0.7931 0.00850 0.00290 -0.1272 0.5989 0.7090
1.750 0.8536 0.00805 0.00297 -0.1280 0.5926 1.0000
2.000 0.8820 0.00812 0.00299 -0.1282 0.5893 1.0000
2.250 0.9102 0.00819 0.00301 -0.1283 0.5862 1.0000
2.500 0.9384 0.00827 0.00304 -0.1285 0.5831 1.0000
2.750 0.9666 0.00834 0.00312 -0.1287 0.5792 1.0000
3.000 0.9947 0.00842 0.00317 -0.1288 0.5750 1.0000
3.250 1.0225 0.00851 0.00322 -0.1289 0.5712 1.0000
3.500 1.0504 0.00860 0.00330 -0.1290 0.5672 1.0000
3.750 1.0781 0.00869 0.00339 -0.1292 0.5625 1.0000
4.000 1.1056 0.00879 0.00347 -0.1292 0.5577 1.0000
4.250 1.1330 0.00891 0.00357 -0.1293 0.5531 1.0000
4.500 1.1604 0.00902 0.00369 -0.1294 0.5475 1.0000
4.750 1.1873 0.00915 0.00379 -0.1294 0.5419 1.0000
5.000 1.2143 0.00928 0.00393 -0.1294 0.5362 1.0000
5.250 1.2409 0.00942 0.00408 -0.1294 0.5298 1.0000
5.500 1.2671 0.00959 0.00423 -0.1293 0.5235 1.0000
5.750 1.2933 0.00976 0.00440 -0.1292 0.5160 1.0000
6.000 1.3188 0.00996 0.00459 -0.1291 0.5085 1.0000
6.250 1.3441 0.01016 0.00480 -0.1289 0.4996 1.0000
6.500 1.3688 0.01039 0.00502 -0.1286 0.4909 1.0000
6.750 1.3925 0.01067 0.00528 -0.1282 0.4812 1.0000
7.000 1.4164 0.01093 0.00555 -0.1278 0.4706 1.0000
7.250 1.4390 0.01124 0.00585 -0.1272 0.4598 1.0000
7.500 1.4602 0.01162 0.00619 -0.1264 0.4476 1.0000
7.750 1.4800 0.01203 0.00659 -0.1254 0.4346 1.0000
8.000 1.4980 0.01251 0.00703 -0.1242 0.4205 1.0000
8.250 1.5135 0.01306 0.00754 -0.1226 0.4055 1.0000
8.500 1.5258 0.01368 0.00813 -0.1205 0.3902 1.0000
8.750 1.5305 0.01442 0.00883 -0.1171 0.3757 1.0000
9.000 1.5331 0.01537 0.00976 -0.1139 0.3615 1.0000
9.250 1.5354 0.01658 0.01092 -0.1111 0.3465 1.0000
9.500 1.5377 0.01795 0.01226 -0.1086 0.3311 1.0000
9.750 1.5393 0.01950 0.01375 -0.1063 0.3148 1.0000
10.000 1.5416 0.02108 0.01530 -0.1041 0.2994 1.0000
10.250 1.5431 0.02277 0.01694 -0.1020 0.2837 1.0000
10.500 1.5439 0.02457 0.01868 -0.1000 0.2671 1.0000
10.750 1.5447 0.02640 0.02046 -0.0980 0.2514 1.0000
11.000 1.5455 0.02829 0.02230 -0.0961 0.2358 1.0000
11.250 1.5469 0.03016 0.02413 -0.0943 0.2215 1.0000
11.500 1.5476 0.03213 0.02606 -0.0926 0.2070 1.0000
11.750 1.5489 0.03409 0.02799 -0.0910 0.1935 1.0000
12.000 1.5501 0.03616 0.03001 -0.0896 0.1792 1.0000
12.250 1.5513 0.03831 0.03212 -0.0882 0.1658 1.0000
12.500 1.5524 0.04053 0.03429 -0.0869 0.1516 1.0000
12.750 1.5543 0.04275 0.03648 -0.0858 0.1396 1.0000
13.000 1.5563 0.04500 0.03870 -0.0848 0.1283 1.0000
13.250 1.5576 0.04738 0.04105 -0.0838 0.1165 1.0000
13.500 1.5592 0.04980 0.04345 -0.0829 0.1055 1.0000
13.750 1.5621 0.05214 0.04578 -0.0821 0.0957 1.0000
14.000 1.5642 0.05462 0.04825 -0.0814 0.0869 1.0000
14.250 1.5659 0.05717 0.05080 -0.0808 0.0786 1.0000
14.500 1.5669 0.05989 0.05351 -0.0803 0.0708 1.0000
14.750 1.5693 0.06247 0.05611 -0.0798 0.0635 1.0000
15.000 1.5706 0.06524 0.05890 -0.0794 0.0575 1.0000
15.250 1.5712 0.06816 0.06182 -0.0791 0.0515 1.0000
15.500 1.5738 0.07090 0.06460 -0.0790 0.0470 1.0000
15.750 1.5742 0.07393 0.06766 -0.0788 0.0427 1.0000
16.000 1.5767 0.07675 0.07054 -0.0788 0.0391 1.0000
16.250 1.5761 0.08003 0.07385 -0.0788 0.0355 1.0000
16.500 1.5785 0.08295 0.07684 -0.0790 0.0328 1.0000
16.750 1.5778 0.08637 0.08030 -0.0792 0.0301 1.0000
17.000 1.5790 0.08952 0.08353 -0.0795 0.0278 1.0000
17.250 1.5787 0.09295 0.08701 -0.0799 0.0257 1.0000
17.500 1.5777 0.09651 0.09063 -0.0804 0.0238 1.0000
17.750 1.5784 0.09988 0.09410 -0.0810 0.0222 1.0000
18.000 1.5769 0.10363 0.09791 -0.0817 0.0207 1.0000
18.250 1.5756 0.10734 0.10170 -0.0825 0.0194 1.0000
18.500 1.5751 0.11097 0.10542 -0.0834 0.0182 1.0000
18.750 1.5734 0.11484 0.10937 -0.0844 0.0171 1.0000
19.000 1.5708 0.11887 0.11346 -0.0855 0.0162 1.0000
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Polar data table (+)
Polar graphs
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