DAE-31 AIRFOIL (dae31-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: DAE-31 AIRFOIL (dae31-il) Reynolds number: 200,000 Max Cl/Cd: 90.85 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dae31-il-200000-n5.txt Download as CSV file: xf-dae31-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DAE-31 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 0.0327 0.09114 0.08672 -0.1007 0.8420 0.0281
-8.500 0.0395 0.08874 0.08433 -0.1018 0.8387 0.0288
-8.250 0.0453 0.08633 0.08195 -0.1030 0.8350 0.0293
-8.000 0.0482 0.08391 0.07955 -0.1046 0.8311 0.0297
-7.750 0.0489 0.08139 0.07705 -0.1064 0.8273 0.0298
-7.500 0.0628 0.07892 0.07457 -0.1059 0.8249 0.0303
-7.250 0.0716 0.07676 0.07239 -0.1063 0.8223 0.0307
-7.000 0.0789 0.07478 0.07046 -0.1068 0.8184 0.0320
-6.750 0.0762 0.07262 0.06836 -0.1081 0.8135 0.0335
-6.500 0.0763 0.06971 0.06546 -0.1122 0.8090 0.0338
-6.250 0.0903 0.06774 0.06348 -0.1108 0.8067 0.0343
-6.000 0.1019 0.06544 0.06116 -0.1120 0.8042 0.0348
-5.750 0.1129 0.06307 0.05882 -0.1141 0.7999 0.0354
-5.500 0.1258 0.06039 0.05615 -0.1169 0.7957 0.0360
-5.000 0.1619 0.04986 0.04545 -0.1300 0.7885 0.0265
-4.500 0.2161 0.03629 0.03138 -0.1448 0.7815 0.0227
-4.250 0.2452 0.02911 0.02358 -0.1503 0.7777 0.0228
-4.000 0.2698 0.02927 0.02380 -0.1503 0.7745 0.0235
-3.750 0.2983 0.02636 0.02049 -0.1521 0.7717 0.0246
-3.500 0.3278 0.02298 0.01648 -0.1536 0.7694 0.0248
-3.250 0.3561 0.02086 0.01386 -0.1542 0.7665 0.0251
-3.000 0.3830 0.01943 0.01205 -0.1543 0.7621 0.0256
-2.750 0.4106 0.01833 0.01063 -0.1542 0.7585 0.0262
-2.500 0.4383 0.01767 0.00989 -0.1542 0.7553 0.0270
-2.250 0.4666 0.01709 0.00918 -0.1542 0.7526 0.0286
-2.000 0.4951 0.01651 0.00847 -0.1542 0.7501 0.0305
-1.750 0.5207 0.01618 0.00814 -0.1539 0.7451 0.0319
-1.500 0.5478 0.01573 0.00762 -0.1537 0.7410 0.0335
-1.250 0.5758 0.01532 0.00721 -0.1536 0.7375 0.0354
-1.000 0.6044 0.01497 0.00680 -0.1536 0.7346 0.0390
-0.750 0.6314 0.01474 0.00657 -0.1534 0.7303 0.0432
-0.500 0.6579 0.01454 0.00639 -0.1532 0.7252 0.0485
-0.250 0.6858 0.01428 0.00614 -0.1531 0.7210 0.0585
0.000 0.7145 0.01397 0.00586 -0.1531 0.7175 0.0775
0.250 0.7410 0.01376 0.00582 -0.1529 0.7125 0.1224
0.750 0.7944 0.01309 0.00580 -0.1528 0.7024 0.3548
1.000 0.8210 0.01270 0.00579 -0.1525 0.6981 0.5122
1.500 0.8754 0.01189 0.00574 -0.1518 0.6862 1.0000
1.750 0.9034 0.01192 0.00564 -0.1516 0.6810 1.0000
2.000 0.9289 0.01205 0.00572 -0.1512 0.6736 1.0000
2.250 0.9568 0.01206 0.00562 -0.1510 0.6677 1.0000
2.500 0.9825 0.01218 0.00570 -0.1506 0.6601 1.0000
2.750 1.0093 0.01224 0.00568 -0.1503 0.6526 1.0000
3.000 1.0353 0.01234 0.00572 -0.1498 0.6447 1.0000
3.250 1.0613 0.01244 0.00575 -0.1494 0.6362 1.0000
3.500 1.0869 0.01256 0.00583 -0.1490 0.6275 1.0000
3.750 1.1127 0.01267 0.00588 -0.1485 0.6183 1.0000
4.000 1.1373 0.01283 0.00601 -0.1479 0.6085 1.0000
4.250 1.1628 0.01297 0.00607 -0.1474 0.5987 1.0000
4.500 1.1864 0.01316 0.00624 -0.1466 0.5871 1.0000
4.750 1.2102 0.01336 0.00639 -0.1459 0.5756 1.0000
5.000 1.2337 0.01358 0.00653 -0.1451 0.5638 1.0000
5.250 1.2563 0.01383 0.00675 -0.1442 0.5509 1.0000
5.500 1.2780 0.01412 0.00699 -0.1431 0.5378 1.0000
5.750 1.2993 0.01442 0.00724 -0.1420 0.5248 1.0000
6.000 1.3197 0.01476 0.00751 -0.1408 0.5116 1.0000
6.500 1.3574 0.01551 0.00819 -0.1378 0.4841 1.0000
6.750 1.3748 0.01593 0.00857 -0.1361 0.4704 1.0000
7.000 1.3903 0.01637 0.00898 -0.1341 0.4569 1.0000
7.250 1.4032 0.01687 0.00942 -0.1317 0.4432 1.0000
7.750 1.4267 0.01801 0.01050 -0.1268 0.4150 1.0000
8.000 1.4382 0.01866 0.01113 -0.1244 0.4008 1.0000
8.250 1.4491 0.01938 0.01181 -0.1221 0.3868 1.0000
8.500 1.4595 0.02016 0.01257 -0.1198 0.3729 1.0000
8.750 1.4694 0.02100 0.01338 -0.1176 0.3592 1.0000
9.000 1.4793 0.02189 0.01424 -0.1154 0.3457 1.0000
9.250 1.4893 0.02281 0.01515 -0.1134 0.3316 1.0000
9.500 1.4990 0.02379 0.01612 -0.1114 0.3182 1.0000
9.750 1.5082 0.02484 0.01715 -0.1094 0.3052 1.0000
10.000 1.5164 0.02598 0.01827 -0.1073 0.2922 1.0000
10.250 1.5242 0.02718 0.01944 -0.1054 0.2797 1.0000
10.500 1.5332 0.02835 0.02063 -0.1036 0.2671 1.0000
10.750 1.5410 0.02962 0.02190 -0.1018 0.2550 1.0000
11.000 1.5483 0.03098 0.02325 -0.1000 0.2437 1.0000
11.250 1.5543 0.03245 0.02472 -0.0981 0.2323 1.0000
11.500 1.5623 0.03383 0.02612 -0.0966 0.2210 1.0000
11.750 1.5686 0.03537 0.02768 -0.0950 0.2105 1.0000
12.000 1.5735 0.03706 0.02937 -0.0933 0.2005 1.0000
12.250 1.5800 0.03869 0.03102 -0.0919 0.1902 1.0000
12.500 1.5857 0.04043 0.03279 -0.0905 0.1808 1.0000
12.750 1.5896 0.04238 0.03475 -0.0891 0.1718 1.0000
13.000 1.5952 0.04425 0.03666 -0.0879 0.1625 1.0000
13.250 1.5999 0.04623 0.03868 -0.0868 0.1541 1.0000
13.500 1.6024 0.04850 0.04096 -0.0856 0.1460 1.0000
13.750 1.6079 0.05053 0.04306 -0.0847 0.1382 1.0000
14.000 1.6108 0.05288 0.04545 -0.0838 0.1313 1.0000
14.250 1.6145 0.05521 0.04784 -0.0830 0.1243 1.0000
14.500 1.6174 0.05767 0.05037 -0.0823 0.1180 1.0000
14.750 1.6193 0.06032 0.05307 -0.0817 0.1118 1.0000
15.000 1.6218 0.06295 0.05578 -0.0811 0.1059 1.0000
15.250 1.6218 0.06594 0.05881 -0.0807 0.1003 1.0000
15.500 1.6238 0.06875 0.06172 -0.0804 0.0945 1.0000
15.750 1.6222 0.07208 0.06510 -0.0803 0.0890 1.0000
16.000 1.6219 0.07533 0.06842 -0.0802 0.0830 1.0000
16.250 1.6209 0.07872 0.07190 -0.0803 0.0776 1.0000
16.500 1.6174 0.08254 0.07577 -0.0806 0.0724 1.0000
16.750 1.6158 0.08615 0.07946 -0.0809 0.0673 1.0000
17.000 1.6127 0.09006 0.08345 -0.0814 0.0628 1.0000
17.250 1.6080 0.09426 0.08772 -0.0821 0.0587 1.0000
17.500 1.6053 0.09822 0.09180 -0.0829 0.0548 1.0000
17.750 1.6000 0.10265 0.09631 -0.0839 0.0516 1.0000
18.000 1.5959 0.10694 0.10071 -0.0850 0.0484 1.0000
18.250 1.5900 0.11158 0.10545 -0.0864 0.0457 1.0000
18.500 1.5851 0.11612 0.11010 -0.0878 0.0430 1.0000
18.750 1.5786 0.12099 0.11506 -0.0896 0.0408 1.0000
19.000 1.5737 0.12561 0.11980 -0.0913 0.0385 1.0000
|
Polar data table (+)
Polar graphs
<< Back to DAE-31 AIRFOIL (dae31-il)