DAE-21 AIRFOIL (dae21-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: DAE-21 AIRFOIL (dae21-il) Reynolds number: 500,000 Max Cl/Cd: 136.48 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dae21-il-500000.txt Download as CSV file: xf-dae21-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.0253 0.09115 0.08804 -0.0652 0.7551 0.0185
-9.250 -0.0178 0.08818 0.08506 -0.0662 0.7530 0.0188
-9.000 -0.0528 0.09395 0.09059 -0.0743 0.7621 0.0184
-8.750 -0.0439 0.09149 0.08815 -0.0754 0.7594 0.0187
-8.500 -0.0355 0.08898 0.08564 -0.0766 0.7568 0.0192
-8.250 -0.0279 0.08639 0.08306 -0.0778 0.7543 0.0195
-8.000 -0.0208 0.08373 0.08039 -0.0791 0.7518 0.0201
-7.750 -0.0226 0.08048 0.07714 -0.0819 0.7490 0.0210
-7.500 -0.0260 0.07699 0.07368 -0.0849 0.7460 0.0212
-7.250 -0.0168 0.07431 0.07104 -0.0848 0.7436 0.0214
-7.000 -0.0055 0.07231 0.06905 -0.0847 0.7409 0.0216
-6.750 0.0012 0.07029 0.06705 -0.0850 0.7381 0.0218
-6.500 0.0096 0.06806 0.06481 -0.0863 0.7354 0.0221
-6.250 0.0196 0.06553 0.06227 -0.0884 0.7328 0.0227
-6.000 0.0311 0.06272 0.05943 -0.0915 0.7302 0.0236
-5.750 0.0512 0.05411 0.05077 -0.1074 0.7272 0.0250
-5.500 0.0635 0.05232 0.04901 -0.1066 0.7244 0.0253
-5.250 0.0817 0.05013 0.04680 -0.1082 0.7216 0.0256
-5.000 0.1024 0.04761 0.04424 -0.1107 0.7190 0.0261
-4.750 0.1262 0.04428 0.04081 -0.1147 0.7166 0.0269
-4.500 0.1614 0.03482 0.03089 -0.1250 0.7143 0.0296
-4.250 0.1844 0.03355 0.02962 -0.1258 0.7118 0.0301
-4.000 0.2180 0.02953 0.02498 -0.1292 0.7091 0.0340
-3.750 0.2414 0.02647 0.02194 -0.1305 0.7064 0.0348
-3.500 0.2674 0.02530 0.02074 -0.1311 0.7036 0.0358
-3.000 0.3284 0.01737 0.01144 -0.1328 0.6991 0.0298
-2.750 0.3570 0.01566 0.00948 -0.1329 0.6965 0.0274
-2.500 0.3860 0.01430 0.00788 -0.1330 0.6938 0.0270
-2.250 0.4147 0.01350 0.00694 -0.1330 0.6908 0.0276
-2.000 0.4434 0.01288 0.00620 -0.1330 0.6879 0.0283
-1.750 0.4722 0.01242 0.00562 -0.1330 0.6851 0.0294
-1.500 0.5005 0.01193 0.00513 -0.1331 0.6826 0.0312
-1.250 0.5291 0.01163 0.00478 -0.1332 0.6798 0.0326
-1.000 0.5577 0.01136 0.00450 -0.1333 0.6767 0.0341
-0.750 0.5862 0.01096 0.00414 -0.1334 0.6733 0.0366
-0.500 0.6150 0.01073 0.00389 -0.1335 0.6702 0.0406
-0.250 0.6438 0.01053 0.00367 -0.1336 0.6673 0.0462
0.000 0.6727 0.01032 0.00347 -0.1337 0.6644 0.0623
0.250 0.7008 0.00981 0.00342 -0.1340 0.6609 0.1954
0.500 0.7286 0.00938 0.00347 -0.1343 0.6572 0.3737
0.750 0.7557 0.00896 0.00352 -0.1343 0.6537 0.5595
1.000 0.7838 0.00805 0.00349 -0.1341 0.6506 1.0000
1.250 0.8124 0.00813 0.00348 -0.1342 0.6472 1.0000
1.500 0.8407 0.00817 0.00349 -0.1343 0.6430 1.0000
1.750 0.8692 0.00821 0.00347 -0.1343 0.6389 1.0000
2.000 0.8977 0.00825 0.00344 -0.1344 0.6352 1.0000
2.250 0.9261 0.00834 0.00346 -0.1345 0.6312 1.0000
2.500 0.9541 0.00839 0.00351 -0.1345 0.6263 1.0000
2.750 0.9823 0.00843 0.00351 -0.1346 0.6217 1.0000
3.000 1.0106 0.00852 0.00351 -0.1346 0.6175 1.0000
3.250 1.0383 0.00859 0.00360 -0.1347 0.6122 1.0000
3.500 1.0661 0.00864 0.00364 -0.1347 0.6068 1.0000
3.750 1.0940 0.00874 0.00366 -0.1347 0.6019 1.0000
4.000 1.1213 0.00882 0.00377 -0.1347 0.5959 1.0000
4.250 1.1488 0.00890 0.00383 -0.1347 0.5898 1.0000
4.500 1.1761 0.00901 0.00391 -0.1346 0.5841 1.0000
4.750 1.2031 0.00910 0.00404 -0.1346 0.5772 1.0000
5.000 1.2301 0.00924 0.00411 -0.1345 0.5709 1.0000
5.250 1.2568 0.00935 0.00426 -0.1344 0.5634 1.0000
5.500 1.2832 0.00949 0.00437 -0.1342 0.5561 1.0000
5.750 1.3094 0.00963 0.00454 -0.1341 0.5478 1.0000
6.250 1.3607 0.00997 0.00487 -0.1336 0.5298 1.0000
6.500 1.3857 0.01018 0.00506 -0.1332 0.5203 1.0000
6.750 1.4101 0.01041 0.00527 -0.1328 0.5098 1.0000
7.000 1.4343 0.01064 0.00551 -0.1324 0.4985 1.0000
7.250 1.4575 0.01092 0.00578 -0.1318 0.4866 1.0000
7.500 1.4796 0.01124 0.00607 -0.1310 0.4738 1.0000
7.750 1.5007 0.01161 0.00640 -0.1301 0.4603 1.0000
8.000 1.5207 0.01201 0.00677 -0.1291 0.4460 1.0000
8.250 1.5396 0.01243 0.00717 -0.1278 0.4312 1.0000
8.500 1.5568 0.01291 0.00761 -0.1264 0.4161 1.0000
8.750 1.5718 0.01344 0.00811 -0.1246 0.4009 1.0000
9.000 1.5819 0.01404 0.00868 -0.1219 0.3851 1.0000
9.250 1.5878 0.01475 0.00936 -0.1187 0.3701 1.0000
9.500 1.5925 0.01565 0.01021 -0.1157 0.3545 1.0000
9.750 1.5974 0.01669 0.01120 -0.1130 0.3386 1.0000
10.000 1.6020 0.01786 0.01233 -0.1105 0.3224 1.0000
10.250 1.6069 0.01911 0.01353 -0.1082 0.3068 1.0000
10.500 1.6108 0.02049 0.01486 -0.1059 0.2907 1.0000
10.750 1.6149 0.02193 0.01625 -0.1037 0.2751 1.0000
11.000 1.6183 0.02347 0.01774 -0.1016 0.2596 1.0000
11.250 1.6220 0.02505 0.01928 -0.0997 0.2445 1.0000
11.500 1.6245 0.02675 0.02093 -0.0977 0.2292 1.0000
11.750 1.6279 0.02845 0.02259 -0.0959 0.2151 1.0000
12.000 1.6309 0.03022 0.02433 -0.0942 0.2013 1.0000
12.250 1.6331 0.03209 0.02616 -0.0925 0.1874 1.0000
12.500 1.6354 0.03401 0.02805 -0.0909 0.1740 1.0000
12.750 1.6373 0.03605 0.03006 -0.0895 0.1611 1.0000
13.000 1.6394 0.03814 0.03212 -0.0881 0.1489 1.0000
13.250 1.6414 0.04032 0.03427 -0.0869 0.1376 1.0000
13.500 1.6427 0.04263 0.03656 -0.0857 0.1270 1.0000
13.750 1.6434 0.04506 0.03897 -0.0846 0.1166 1.0000
14.000 1.6454 0.04744 0.04133 -0.0837 0.1074 1.0000
14.250 1.6472 0.04988 0.04379 -0.0828 0.0988 1.0000
14.500 1.6483 0.05246 0.04637 -0.0820 0.0912 1.0000
14.750 1.6483 0.05525 0.04915 -0.0814 0.0839 1.0000
15.000 1.6505 0.05785 0.05179 -0.0808 0.0778 1.0000
15.250 1.6494 0.06088 0.05483 -0.0803 0.0721 1.0000
15.500 1.6513 0.06363 0.05763 -0.0800 0.0671 1.0000
15.750 1.6495 0.06689 0.06091 -0.0797 0.0624 1.0000
16.000 1.6510 0.06980 0.06388 -0.0796 0.0583 1.0000
16.250 1.6468 0.07351 0.06761 -0.0795 0.0544 1.0000
16.500 1.6489 0.07644 0.07063 -0.0796 0.0512 1.0000
16.750 1.6456 0.08017 0.07440 -0.0798 0.0482 1.0000
17.000 1.6438 0.08378 0.07809 -0.0800 0.0455 1.0000
17.250 1.6426 0.08734 0.08173 -0.0804 0.0432 1.0000
17.500 1.6372 0.09156 0.08599 -0.0810 0.0410 1.0000
17.750 1.6343 0.09551 0.09002 -0.0817 0.0391 1.0000
18.000 1.6328 0.09929 0.09390 -0.0824 0.0373 1.0000
18.250 1.6283 0.10357 0.09824 -0.0834 0.0357 1.0000
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Polar data table (+)
Polar graphs
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