DAE-31 AIRFOIL (dae31-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: DAE-31 AIRFOIL (dae31-il) Reynolds number: 1,000,000 Max Cl/Cd: 151.47 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-dae31-il-1000000-n5.txt Download as CSV file: xf-dae31-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0025 0.09468 0.09189 -0.0966 0.7825 0.0098
-9.500 0.0028 0.09130 0.08852 -0.0980 0.7804 0.0093
-7.000 -0.0486 0.01754 0.01346 -0.1509 0.7489 0.0110
-6.750 -0.0228 0.01579 0.01141 -0.1517 0.7466 0.0111
-6.500 0.0042 0.01472 0.01013 -0.1521 0.7439 0.0112
-6.250 0.0308 0.01347 0.00865 -0.1525 0.7411 0.0115
-6.000 0.0584 0.01280 0.00785 -0.1528 0.7384 0.0117
-5.750 0.0862 0.01230 0.00724 -0.1529 0.7356 0.0118
-5.500 0.1142 0.01190 0.00675 -0.1531 0.7328 0.0120
-5.250 0.1425 0.01146 0.00624 -0.1532 0.7301 0.0122
-5.000 0.1708 0.01107 0.00577 -0.1534 0.7269 0.0124
-4.750 0.1991 0.01068 0.00530 -0.1535 0.7237 0.0126
-4.500 0.2274 0.01032 0.00486 -0.1536 0.7204 0.0128
-4.250 0.2557 0.01000 0.00444 -0.1537 0.7173 0.0130
-4.000 0.2842 0.00970 0.00407 -0.1538 0.7144 0.0133
-3.750 0.3129 0.00941 0.00374 -0.1539 0.7112 0.0135
-3.500 0.3415 0.00920 0.00347 -0.1540 0.7076 0.0138
-3.250 0.3699 0.00892 0.00316 -0.1541 0.7038 0.0143
-3.000 0.3982 0.00876 0.00295 -0.1541 0.7001 0.0148
-2.750 0.4270 0.00858 0.00276 -0.1542 0.6965 0.0152
-2.500 0.4556 0.00842 0.00257 -0.1543 0.6923 0.0157
-2.250 0.4842 0.00828 0.00239 -0.1544 0.6877 0.0162
-2.000 0.5125 0.00816 0.00222 -0.1544 0.6831 0.0167
-1.750 0.5412 0.00801 0.00207 -0.1545 0.6788 0.0175
-1.500 0.5697 0.00791 0.00196 -0.1545 0.6737 0.0183
-1.250 0.5980 0.00784 0.00185 -0.1546 0.6683 0.0193
-1.000 0.6264 0.00776 0.00176 -0.1546 0.6632 0.0206
-0.750 0.6549 0.00770 0.00169 -0.1547 0.6574 0.0224
-0.500 0.6830 0.00766 0.00163 -0.1546 0.6510 0.0248
-0.250 0.7113 0.00761 0.00158 -0.1547 0.6450 0.0281
0.000 0.7393 0.00758 0.00155 -0.1547 0.6375 0.0334
0.250 0.7672 0.00756 0.00153 -0.1547 0.6302 0.0437
0.500 0.7950 0.00754 0.00153 -0.1546 0.6214 0.0591
0.750 0.8225 0.00752 0.00155 -0.1546 0.6126 0.0822
1.000 0.8499 0.00750 0.00158 -0.1545 0.6023 0.1198
1.250 0.8771 0.00747 0.00163 -0.1545 0.5923 0.1651
1.500 0.9038 0.00744 0.00171 -0.1543 0.5817 0.2404
1.750 0.9307 0.00738 0.00181 -0.1543 0.5705 0.3289
2.000 0.9572 0.00738 0.00192 -0.1541 0.5597 0.4004
2.250 0.9830 0.00739 0.00206 -0.1538 0.5476 0.4888
2.500 1.0080 0.00722 0.00223 -0.1535 0.5349 0.6593
3.000 1.0603 0.00700 0.00250 -0.1529 0.5085 1.0000
3.250 1.0856 0.00722 0.00263 -0.1524 0.4949 1.0000
3.750 1.1359 0.00766 0.00292 -0.1515 0.4678 1.0000
4.000 1.1607 0.00788 0.00307 -0.1511 0.4546 1.0000
4.250 1.1850 0.00813 0.00325 -0.1505 0.4413 1.0000
4.500 1.2087 0.00840 0.00343 -0.1498 0.4273 1.0000
4.750 1.2323 0.00866 0.00363 -0.1491 0.4136 1.0000
5.000 1.2557 0.00892 0.00383 -0.1484 0.3998 1.0000
5.250 1.2783 0.00921 0.00405 -0.1476 0.3857 1.0000
5.500 1.3001 0.00953 0.00429 -0.1466 0.3713 1.0000
5.750 1.3210 0.00987 0.00455 -0.1455 0.3561 1.0000
6.000 1.3410 0.01022 0.00483 -0.1442 0.3408 1.0000
6.250 1.3603 0.01059 0.00513 -0.1428 0.3266 1.0000
6.500 1.3787 0.01096 0.00543 -0.1413 0.3127 1.0000
6.750 1.3946 0.01131 0.00573 -0.1393 0.2998 1.0000
7.000 1.4089 0.01170 0.00608 -0.1369 0.2879 1.0000
7.250 1.4221 0.01216 0.00649 -0.1345 0.2752 1.0000
7.750 1.4502 0.01314 0.00737 -0.1303 0.2520 1.0000
8.000 1.4643 0.01368 0.00787 -0.1283 0.2411 1.0000
8.250 1.4775 0.01430 0.00844 -0.1263 0.2295 1.0000
8.500 1.4911 0.01492 0.00902 -0.1244 0.2181 1.0000
8.750 1.5048 0.01557 0.00963 -0.1226 0.2070 1.0000
9.000 1.5182 0.01627 0.01029 -0.1208 0.1966 1.0000
9.250 1.5309 0.01702 0.01101 -0.1190 0.1865 1.0000
9.500 1.5452 0.01771 0.01167 -0.1174 0.1776 1.0000
9.750 1.5573 0.01854 0.01246 -0.1156 0.1670 1.0000
10.000 1.5691 0.01941 0.01329 -0.1138 0.1574 1.0000
10.250 1.5804 0.02033 0.01418 -0.1121 0.1470 1.0000
10.500 1.5911 0.02131 0.01511 -0.1103 0.1360 1.0000
10.750 1.6013 0.02235 0.01611 -0.1085 0.1256 1.0000
11.000 1.6113 0.02342 0.01714 -0.1067 0.1156 1.0000
11.250 1.6211 0.02453 0.01822 -0.1050 0.1075 1.0000
11.500 1.6316 0.02561 0.01928 -0.1035 0.1005 1.0000
11.750 1.6415 0.02676 0.02042 -0.1019 0.0934 1.0000
12.000 1.6515 0.02792 0.02157 -0.1004 0.0874 1.0000
12.250 1.6595 0.02926 0.02289 -0.0988 0.0808 1.0000
12.500 1.6678 0.03062 0.02423 -0.0972 0.0737 1.0000
12.750 1.6769 0.03194 0.02556 -0.0959 0.0684 1.0000
13.000 1.6840 0.03347 0.02708 -0.0944 0.0621 1.0000
13.250 1.6912 0.03502 0.02863 -0.0930 0.0569 1.0000
13.500 1.6984 0.03664 0.03025 -0.0917 0.0523 1.0000
13.750 1.7058 0.03827 0.03190 -0.0905 0.0478 1.0000
14.000 1.7122 0.04002 0.03366 -0.0893 0.0437 1.0000
14.250 1.7180 0.04188 0.03554 -0.0882 0.0397 1.0000
14.500 1.7235 0.04382 0.03750 -0.0871 0.0363 1.0000
14.750 1.7289 0.04582 0.03953 -0.0862 0.0332 1.0000
15.000 1.7339 0.04788 0.04162 -0.0853 0.0302 1.0000
15.250 1.7380 0.05011 0.04389 -0.0844 0.0278 1.0000
15.500 1.7427 0.05231 0.04613 -0.0837 0.0256 1.0000
15.750 1.7461 0.05472 0.04859 -0.0830 0.0235 1.0000
16.000 1.7487 0.05727 0.05118 -0.0824 0.0216 1.0000
16.250 1.7527 0.05970 0.05367 -0.0820 0.0202 1.0000
16.500 1.7539 0.06254 0.05655 -0.0816 0.0186 1.0000
16.750 1.7566 0.06522 0.05930 -0.0813 0.0174 1.0000
17.000 1.7570 0.06828 0.06241 -0.0811 0.0160 1.0000
17.250 1.7583 0.07127 0.06548 -0.0810 0.0150 1.0000
17.500 1.7579 0.07453 0.06880 -0.0811 0.0139 1.0000
17.750 1.7580 0.07779 0.07214 -0.0812 0.0129 1.0000
18.000 1.7561 0.08140 0.07582 -0.0815 0.0119 1.0000
18.250 1.7540 0.08512 0.07961 -0.0820 0.0111 1.0000
18.500 1.7523 0.08879 0.08337 -0.0825 0.0103 1.0000
18.750 1.7487 0.09282 0.08747 -0.0832 0.0096 1.0000
19.000 1.7452 0.09691 0.09165 -0.0841 0.0092 1.0000
19.250 1.7415 0.10109 0.09592 -0.0851 0.0087 1.0000
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Polar data table (+)
Polar graphs
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