DAE-21 AIRFOIL (dae21-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: DAE-21 AIRFOIL (dae21-il) Reynolds number: 100,000 Max Cl/Cd: 50.14 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dae21-il-100000-n5.txt Download as CSV file: xf-dae21-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DAE-21 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.0789 0.11438 0.10880 -0.0738 0.8334 0.0452
-10.000 -0.0758 0.11244 0.10687 -0.0761 0.8297 0.0459
-9.750 -0.0751 0.11070 0.10517 -0.0787 0.8253 0.0462
-9.500 -0.0690 0.10794 0.10242 -0.0803 0.8215 0.0464
-9.250 -0.0508 0.10380 0.09825 -0.0795 0.8189 0.0472
-9.000 -0.0403 0.10105 0.09548 -0.0799 0.8162 0.0482
-8.750 -0.0312 0.09855 0.09300 -0.0811 0.8127 0.0492
-8.500 -0.0234 0.09612 0.09058 -0.0824 0.8087 0.0505
-8.250 -0.0172 0.09381 0.08829 -0.0837 0.8049 0.0518
-8.000 -0.0159 0.09190 0.08638 -0.0859 0.8012 0.0533
-7.750 -0.0175 0.09013 0.08464 -0.0888 0.7976 0.0538
-7.500 -0.0183 0.08826 0.08284 -0.0914 0.7926 0.0540
-7.250 -0.0025 0.08450 0.07909 -0.0906 0.7896 0.0547
-7.000 0.0100 0.08178 0.07637 -0.0902 0.7864 0.0556
-6.750 0.0173 0.07958 0.07416 -0.0903 0.7834 0.0565
-6.500 0.0239 0.07747 0.07206 -0.0912 0.7803 0.0578
-6.250 0.0310 0.07532 0.06996 -0.0941 0.7755 0.0609
-6.000 0.0402 0.07227 0.06686 -0.1068 0.7701 0.0632
-5.750 0.0505 0.06933 0.06394 -0.1037 0.7675 0.0643
-5.500 0.0636 0.06727 0.06188 -0.1017 0.7653 0.0666
-5.250 0.0780 0.06479 0.05940 -0.1045 0.7613 0.0687
-4.750 0.1232 0.05164 0.04582 -0.1214 0.7526 0.0400
-4.500 0.1436 0.04908 0.04316 -0.1228 0.7499 0.0385
-4.250 0.1684 0.04528 0.03914 -0.1260 0.7476 0.0371
-4.000 0.1944 0.04083 0.03433 -0.1300 0.7429 0.0355
-3.750 0.2213 0.03710 0.03014 -0.1326 0.7387 0.0351
-3.500 0.2474 0.03516 0.02792 -0.1337 0.7355 0.0366
-3.250 0.2760 0.03270 0.02498 -0.1348 0.7329 0.0377
-3.000 0.3054 0.03043 0.02218 -0.1355 0.7309 0.0380
-2.750 0.3307 0.02902 0.02038 -0.1357 0.7262 0.0384
-2.500 0.3567 0.02782 0.01880 -0.1357 0.7218 0.0391
-2.250 0.3837 0.02687 0.01765 -0.1357 0.7186 0.0409
-2.000 0.4115 0.02612 0.01676 -0.1356 0.7161 0.0436
-1.750 0.4405 0.02519 0.01555 -0.1354 0.7140 0.0456
-1.500 0.4628 0.02490 0.01526 -0.1349 0.7085 0.0472
-1.250 0.4874 0.02457 0.01492 -0.1346 0.7041 0.0503
-1.000 0.5145 0.02409 0.01437 -0.1343 0.7011 0.0552
-0.750 0.5426 0.02358 0.01382 -0.1341 0.6987 0.0605
-0.500 0.5717 0.02307 0.01327 -0.1340 0.6968 0.0698
-0.250 0.5902 0.02343 0.01370 -0.1333 0.6892 0.0819
0.000 0.6167 0.02307 0.01345 -0.1331 0.6857 0.1182
0.250 0.6459 0.02225 0.01327 -0.1335 0.6831 0.3137
0.500 0.6705 0.02114 0.01317 -0.1324 0.6811 0.6587
1.000 0.7187 0.02148 0.01368 -0.1314 0.6700 1.0000
1.250 0.7477 0.02147 0.01348 -0.1313 0.6672 1.0000
1.500 0.7778 0.02139 0.01321 -0.1313 0.6650 1.0000
1.750 0.7941 0.02224 0.01403 -0.1303 0.6570 1.0000
2.000 0.8209 0.02235 0.01403 -0.1300 0.6531 1.0000
2.250 0.8505 0.02227 0.01382 -0.1299 0.6505 1.0000
2.750 0.8937 0.02316 0.01461 -0.1285 0.6391 1.0000
3.000 0.9226 0.02309 0.01446 -0.1284 0.6358 1.0000
3.250 0.9540 0.02287 0.01415 -0.1285 0.6335 1.0000
3.500 0.9663 0.02385 0.01517 -0.1269 0.6246 1.0000
3.750 0.9945 0.02380 0.01507 -0.1267 0.6208 1.0000
4.000 1.0264 0.02352 0.01473 -0.1268 0.6181 1.0000
4.250 1.0381 0.02447 0.01573 -0.1251 0.6092 1.0000
4.500 1.0664 0.02437 0.01561 -0.1249 0.6051 1.0000
4.750 1.0994 0.02400 0.01519 -0.1251 0.6022 1.0000
5.000 1.1085 0.02502 0.01629 -0.1230 0.5926 1.0000
5.250 1.1388 0.02477 0.01604 -0.1230 0.5885 1.0000
5.500 1.1584 0.02514 0.01644 -0.1219 0.5818 1.0000
5.750 1.1789 0.02543 0.01675 -0.1209 0.5749 1.0000
6.000 1.2136 0.02492 0.01622 -0.1213 0.5711 1.0000
6.250 1.2198 0.02596 0.01737 -0.1188 0.5609 1.0000
6.750 1.2592 0.02646 0.01794 -0.1164 0.5462 1.0000
7.000 1.2923 0.02604 0.01755 -0.1166 0.5407 1.0000
7.250 1.2954 0.02707 0.01864 -0.1136 0.5305 1.0000
7.500 1.3301 0.02653 0.01811 -0.1140 0.5244 1.0000
7.750 1.3315 0.02773 0.01939 -0.1110 0.5134 1.0000
8.000 1.3551 0.02776 0.01946 -0.1102 0.5051 1.0000
8.250 1.3706 0.02825 0.01999 -0.1087 0.4950 1.0000
8.500 1.3805 0.02913 0.02093 -0.1068 0.4840 1.0000
8.750 1.4028 0.02923 0.02105 -0.1059 0.4741 1.0000
9.000 1.4188 0.02973 0.02160 -0.1045 0.4627 1.0000
9.250 1.4270 0.03080 0.02272 -0.1027 0.4502 1.0000
9.500 1.4393 0.03161 0.02356 -0.1011 0.4378 1.0000
9.750 1.4536 0.03229 0.02426 -0.0997 0.4253 1.0000
10.000 1.4664 0.03307 0.02506 -0.0982 0.4120 1.0000
10.250 1.4781 0.03396 0.02594 -0.0967 0.3983 1.0000
10.500 1.4844 0.03530 0.02731 -0.0949 0.3839 1.0000
10.750 1.4905 0.03670 0.02874 -0.0932 0.3693 1.0000
11.000 1.4963 0.03816 0.03023 -0.0916 0.3548 1.0000
11.250 1.5015 0.03973 0.03181 -0.0900 0.3402 1.0000
11.500 1.5058 0.04140 0.03349 -0.0885 0.3254 1.0000
11.750 1.5095 0.04318 0.03528 -0.0870 0.3108 1.0000
12.000 1.5125 0.04507 0.03718 -0.0855 0.2966 1.0000
12.250 1.5145 0.04710 0.03923 -0.0842 0.2823 1.0000
12.500 1.5161 0.04924 0.04137 -0.0829 0.2683 1.0000
12.750 1.5170 0.05153 0.04367 -0.0817 0.2545 1.0000
13.000 1.5172 0.05398 0.04613 -0.0806 0.2410 1.0000
13.250 1.5169 0.05658 0.04873 -0.0797 0.2277 1.0000
13.500 1.5162 0.05932 0.05149 -0.0789 0.2149 1.0000
13.750 1.5149 0.06223 0.05444 -0.0782 0.2022 1.0000
14.000 1.5135 0.06524 0.05750 -0.0777 0.1902 1.0000
14.250 1.5117 0.06837 0.06066 -0.0773 0.1787 1.0000
14.500 1.5093 0.07166 0.06396 -0.0770 0.1680 1.0000
14.750 1.5062 0.07511 0.06743 -0.0768 0.1578 1.0000
15.000 1.5039 0.07860 0.07100 -0.0768 0.1478 1.0000
15.250 1.5011 0.08218 0.07464 -0.0769 0.1389 1.0000
15.500 1.4969 0.08600 0.07847 -0.0771 0.1307 1.0000
15.750 1.4946 0.08970 0.08228 -0.0775 0.1224 1.0000
16.000 1.4909 0.09362 0.08623 -0.0779 0.1155 1.0000
16.250 1.4877 0.09756 0.09025 -0.0786 0.1085 1.0000
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Polar data table (+)
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