DAE-31 AIRFOIL (dae31-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: DAE-31 AIRFOIL (dae31-il) Reynolds number: 500,000 Max Cl/Cd: 128.78 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dae31-il-500000-n5.txt Download as CSV file: xf-dae31-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 0.0267 0.08671 0.08334 -0.1001 0.7972 0.0164
-8.500 0.0321 0.08390 0.08054 -0.1014 0.7944 0.0165
-8.250 0.0390 0.08133 0.07798 -0.1025 0.7917 0.0165
-8.000 0.0446 0.07866 0.07530 -0.1036 0.7890 0.0165
-7.750 0.0488 0.07584 0.07247 -0.1047 0.7863 0.0165
-7.250 0.0566 0.06969 0.06637 -0.1061 0.7805 0.0137
-7.000 0.0602 0.06730 0.06400 -0.1066 0.7772 0.0136
-6.750 0.0609 0.06466 0.06137 -0.1074 0.7738 0.0137
-6.500 0.0679 0.06170 0.05840 -0.1097 0.7707 0.0136
-5.500 0.1195 0.02241 0.01803 -0.1498 0.7569 0.0140
-5.250 0.1455 0.01965 0.01487 -0.1514 0.7543 0.0142
-5.000 0.1725 0.01815 0.01308 -0.1522 0.7518 0.0145
-4.750 0.1997 0.01663 0.01126 -0.1528 0.7492 0.0148
-4.500 0.2273 0.01543 0.00981 -0.1532 0.7461 0.0151
-4.250 0.2551 0.01438 0.00852 -0.1535 0.7428 0.0155
-4.000 0.2831 0.01356 0.00747 -0.1536 0.7396 0.0160
-3.750 0.3113 0.01295 0.00664 -0.1537 0.7367 0.0166
-3.500 0.3392 0.01242 0.00602 -0.1538 0.7339 0.0170
-3.250 0.3674 0.01202 0.00558 -0.1539 0.7308 0.0175
-3.000 0.3957 0.01163 0.00513 -0.1540 0.7272 0.0179
-2.750 0.4239 0.01126 0.00469 -0.1540 0.7237 0.0185
-2.500 0.4522 0.01093 0.00428 -0.1540 0.7202 0.0191
-2.250 0.4804 0.01063 0.00390 -0.1540 0.7170 0.0198
-2.000 0.5087 0.01038 0.00366 -0.1541 0.7132 0.0205
-1.750 0.5370 0.01018 0.00345 -0.1542 0.7090 0.0215
-1.500 0.5653 0.01000 0.00323 -0.1542 0.7046 0.0228
-1.250 0.5935 0.00984 0.00305 -0.1542 0.7006 0.0245
-1.000 0.6218 0.00970 0.00289 -0.1542 0.6962 0.0264
-0.750 0.6500 0.00956 0.00276 -0.1542 0.6913 0.0287
-0.500 0.6781 0.00945 0.00263 -0.1542 0.6863 0.0319
-0.250 0.7061 0.00937 0.00253 -0.1542 0.6817 0.0379
0.000 0.7342 0.00927 0.00248 -0.1542 0.6761 0.0480
0.250 0.7620 0.00918 0.00242 -0.1542 0.6703 0.0660
0.500 0.7898 0.00908 0.00239 -0.1541 0.6647 0.0975
0.750 0.8174 0.00896 0.00241 -0.1542 0.6581 0.1480
1.000 0.8447 0.00882 0.00243 -0.1541 0.6513 0.2267
1.500 0.8985 0.00852 0.00259 -0.1540 0.6359 0.4354
1.750 0.9248 0.00838 0.00268 -0.1538 0.6277 0.5448
2.250 0.9786 0.00775 0.00281 -0.1533 0.6091 1.0000
2.500 1.0048 0.00791 0.00287 -0.1529 0.5991 1.0000
2.750 1.0312 0.00804 0.00295 -0.1527 0.5884 1.0000
3.000 1.0571 0.00821 0.00304 -0.1523 0.5778 1.0000
3.250 1.0822 0.00841 0.00316 -0.1518 0.5656 1.0000
3.500 1.1075 0.00860 0.00328 -0.1513 0.5529 1.0000
3.750 1.1322 0.00882 0.00342 -0.1508 0.5400 1.0000
4.000 1.1562 0.00906 0.00359 -0.1501 0.5267 1.0000
4.250 1.1797 0.00933 0.00378 -0.1494 0.5132 1.0000
4.500 1.2029 0.00960 0.00397 -0.1486 0.4993 1.0000
4.750 1.2261 0.00986 0.00418 -0.1479 0.4861 1.0000
5.000 1.2485 0.01015 0.00441 -0.1470 0.4728 1.0000
5.250 1.2700 0.01047 0.00466 -0.1459 0.4592 1.0000
5.500 1.2907 0.01081 0.00493 -0.1447 0.4457 1.0000
5.750 1.3111 0.01114 0.00521 -0.1435 0.4315 1.0000
6.000 1.3306 0.01149 0.00551 -0.1422 0.4174 1.0000
6.250 1.3488 0.01187 0.00584 -0.1406 0.4033 1.0000
6.500 1.3644 0.01229 0.00619 -0.1386 0.3890 1.0000
6.750 1.3775 0.01273 0.00658 -0.1361 0.3752 1.0000
7.000 1.3895 0.01325 0.00703 -0.1335 0.3607 1.0000
7.250 1.4032 0.01375 0.00750 -0.1313 0.3474 1.0000
7.500 1.4166 0.01430 0.00801 -0.1292 0.3343 1.0000
7.750 1.4296 0.01491 0.00858 -0.1271 0.3214 1.0000
8.000 1.4419 0.01560 0.00921 -0.1250 0.3079 1.0000
8.250 1.4539 0.01632 0.00989 -0.1229 0.2948 1.0000
8.500 1.4671 0.01703 0.01057 -0.1211 0.2818 1.0000
8.750 1.4797 0.01780 0.01129 -0.1192 0.2693 1.0000
9.000 1.4921 0.01860 0.01207 -0.1174 0.2575 1.0000
9.250 1.5036 0.01948 0.01290 -0.1155 0.2457 1.0000
9.500 1.5153 0.02037 0.01376 -0.1138 0.2334 1.0000
9.750 1.5274 0.02126 0.01463 -0.1121 0.2221 1.0000
10.000 1.5387 0.02222 0.01557 -0.1104 0.2113 1.0000
10.250 1.5489 0.02328 0.01659 -0.1086 0.2003 1.0000
10.500 1.5601 0.02429 0.01759 -0.1070 0.1897 1.0000
10.750 1.5705 0.02538 0.01866 -0.1053 0.1797 1.0000
11.000 1.5800 0.02656 0.01981 -0.1036 0.1693 1.0000
11.500 1.5981 0.02904 0.02226 -0.1004 0.1495 1.0000
11.750 1.6066 0.03037 0.02357 -0.0989 0.1407 1.0000
12.000 1.6146 0.03177 0.02495 -0.0973 0.1322 1.0000
12.250 1.6234 0.03314 0.02634 -0.0959 0.1246 1.0000
12.500 1.6315 0.03460 0.02781 -0.0945 0.1170 1.0000
12.750 1.6380 0.03624 0.02944 -0.0931 0.1096 1.0000
13.000 1.6454 0.03785 0.03106 -0.0919 0.1019 1.0000
13.250 1.6520 0.03958 0.03279 -0.0906 0.0950 1.0000
13.500 1.6579 0.04140 0.03463 -0.0894 0.0888 1.0000
13.750 1.6624 0.04342 0.03664 -0.0883 0.0813 1.0000
14.000 1.6676 0.04542 0.03865 -0.0872 0.0744 1.0000
14.250 1.6720 0.04754 0.04079 -0.0862 0.0684 1.0000
14.500 1.6762 0.04974 0.04301 -0.0853 0.0631 1.0000
14.750 1.6796 0.05207 0.04537 -0.0845 0.0583 1.0000
15.000 1.6836 0.05441 0.04775 -0.0838 0.0539 1.0000
15.250 1.6870 0.05685 0.05024 -0.0832 0.0499 1.0000
15.500 1.6886 0.05955 0.05298 -0.0826 0.0462 1.0000
15.750 1.6908 0.06225 0.05573 -0.0821 0.0425 1.0000
16.000 1.6923 0.06511 0.05864 -0.0818 0.0393 1.0000
16.250 1.6925 0.06818 0.06177 -0.0816 0.0365 1.0000
16.500 1.6929 0.07128 0.06494 -0.0814 0.0338 1.0000
16.750 1.6928 0.07452 0.06825 -0.0814 0.0315 1.0000
17.000 1.6917 0.07795 0.07175 -0.0816 0.0292 1.0000
17.250 1.6903 0.08150 0.07539 -0.0818 0.0274 1.0000
17.500 1.6884 0.08519 0.07916 -0.0822 0.0257 1.0000
17.750 1.6861 0.08898 0.08303 -0.0827 0.0241 1.0000
18.000 1.6831 0.09293 0.08708 -0.0834 0.0226 1.0000
18.250 1.6790 0.09714 0.09137 -0.0842 0.0214 1.0000
18.500 1.6756 0.10128 0.09562 -0.0852 0.0201 1.0000
18.750 1.6704 0.10575 0.10018 -0.0863 0.0190 1.0000
19.000 1.6662 0.11010 0.10463 -0.0876 0.0181 1.0000
19.250 1.6614 0.11461 0.10924 -0.0890 0.0171 1.0000
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Polar data table (+)
Polar graphs
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