DAE-31 AIRFOIL (dae31-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: DAE-31 AIRFOIL (dae31-il) Reynolds number: 1,000,000 Max Cl/Cd: 173.71 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dae31-il-1000000.txt Download as CSV file: xf-dae31-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.0010 0.09466 0.09206 -0.0995 0.8131 0.0138
-9.500 0.0069 0.09186 0.08925 -0.1009 0.8107 0.0138
-9.250 0.0120 0.08892 0.08630 -0.1023 0.8080 0.0138
-9.000 0.0196 0.08599 0.08335 -0.1032 0.8049 0.0139
-8.750 0.0320 0.08391 0.08128 -0.1036 0.8030 0.0141
-8.500 0.0417 0.08174 0.07913 -0.1043 0.8010 0.0142
-8.250 0.0500 0.07946 0.07686 -0.1052 0.7984 0.0142
-8.000 0.0583 0.07722 0.07463 -0.1060 0.7957 0.0144
-7.750 0.0664 0.07505 0.07246 -0.1068 0.7931 0.0146
-7.500 0.0737 0.07284 0.07024 -0.1075 0.7902 0.0150
-7.250 0.0801 0.07059 0.06798 -0.1082 0.7868 0.0151
-7.000 0.0851 0.06826 0.06568 -0.1088 0.7841 0.0154
-6.750 0.0864 0.06580 0.06324 -0.1091 0.7811 0.0160
-6.500 0.0800 0.06068 0.05815 -0.1139 0.7770 0.0166
-6.250 0.0881 0.05746 0.05493 -0.1161 0.7741 0.0168
-6.000 0.1023 0.05542 0.05287 -0.1179 0.7710 0.0169
-5.750 0.1184 0.05347 0.05089 -0.1198 0.7676 0.0172
-5.500 0.1356 0.05099 0.04841 -0.1226 0.7652 0.0175
-5.250 0.1548 0.04797 0.04539 -0.1264 0.7621 0.0181
-4.750 0.2068 0.01701 0.01281 -0.1535 0.7558 0.0167
-4.500 0.2330 0.01424 0.00955 -0.1543 0.7530 0.0168
-4.250 0.2605 0.01321 0.00835 -0.1546 0.7500 0.0172
-4.000 0.2886 0.01263 0.00770 -0.1548 0.7477 0.0175
-3.750 0.3169 0.01190 0.00685 -0.1549 0.7449 0.0178
-3.500 0.3452 0.01121 0.00603 -0.1551 0.7420 0.0181
-3.250 0.3736 0.01062 0.00531 -0.1551 0.7390 0.0184
-3.000 0.4020 0.01013 0.00470 -0.1552 0.7359 0.0188
-2.750 0.4305 0.00977 0.00424 -0.1552 0.7326 0.0192
-2.500 0.4590 0.00937 0.00379 -0.1553 0.7296 0.0198
-2.250 0.4874 0.00896 0.00337 -0.1554 0.7261 0.0205
-2.000 0.5159 0.00870 0.00310 -0.1554 0.7225 0.0213
-1.750 0.5445 0.00850 0.00284 -0.1555 0.7189 0.0222
-1.500 0.5730 0.00827 0.00257 -0.1555 0.7151 0.0231
-1.250 0.6016 0.00806 0.00238 -0.1556 0.7114 0.0244
-1.000 0.6303 0.00792 0.00222 -0.1557 0.7072 0.0260
-0.750 0.6588 0.00776 0.00204 -0.1557 0.7030 0.0282
-0.500 0.6872 0.00767 0.00193 -0.1558 0.6986 0.0315
-0.250 0.7158 0.00754 0.00183 -0.1558 0.6942 0.0366
0.000 0.7443 0.00742 0.00174 -0.1559 0.6892 0.0484
0.250 0.7724 0.00730 0.00169 -0.1559 0.6840 0.0793
0.500 0.8006 0.00713 0.00168 -0.1560 0.6788 0.1359
0.750 0.8287 0.00697 0.00170 -0.1561 0.6727 0.2105
1.000 0.8561 0.00683 0.00173 -0.1561 0.6665 0.3053
1.250 0.8840 0.00665 0.00180 -0.1563 0.6602 0.4111
1.500 0.9108 0.00642 0.00189 -0.1562 0.6532 0.5632
1.750 0.9383 0.00567 0.00199 -0.1561 0.6464 1.0000
2.000 0.9662 0.00574 0.00202 -0.1561 0.6385 1.0000
2.250 0.9935 0.00585 0.00205 -0.1559 0.6303 1.0000
2.500 1.0209 0.00594 0.00210 -0.1558 0.6209 1.0000
2.750 1.0480 0.00606 0.00216 -0.1557 0.6112 1.0000
3.000 1.0745 0.00621 0.00223 -0.1554 0.6002 1.0000
3.250 1.1013 0.00634 0.00231 -0.1552 0.5891 1.0000
3.500 1.1275 0.00650 0.00241 -0.1549 0.5776 1.0000
3.750 1.1531 0.00669 0.00253 -0.1545 0.5651 1.0000
4.000 1.1790 0.00686 0.00265 -0.1542 0.5523 1.0000
4.250 1.2045 0.00705 0.00279 -0.1538 0.5397 1.0000
4.500 1.2294 0.00727 0.00294 -0.1534 0.5267 1.0000
4.750 1.2538 0.00751 0.00311 -0.1528 0.5134 1.0000
5.000 1.2781 0.00774 0.00329 -0.1522 0.4997 1.0000
5.250 1.3023 0.00798 0.00347 -0.1516 0.4860 1.0000
5.500 1.3257 0.00824 0.00367 -0.1509 0.4719 1.0000
5.750 1.3484 0.00852 0.00389 -0.1501 0.4574 1.0000
6.000 1.3705 0.00883 0.00413 -0.1492 0.4427 1.0000
6.250 1.3919 0.00915 0.00438 -0.1482 0.4281 1.0000
6.500 1.4128 0.00947 0.00464 -0.1470 0.4132 1.0000
6.750 1.4333 0.00979 0.00491 -0.1459 0.3987 1.0000
7.000 1.4527 0.01014 0.00521 -0.1445 0.3842 1.0000
7.250 1.4707 0.01051 0.00552 -0.1429 0.3697 1.0000
7.500 1.4854 0.01090 0.00586 -0.1406 0.3555 1.0000
7.750 1.4977 0.01134 0.00623 -0.1379 0.3417 1.0000
8.000 1.5092 0.01184 0.00668 -0.1353 0.3276 1.0000
8.250 1.5219 0.01235 0.00714 -0.1329 0.3137 1.0000
8.500 1.5344 0.01291 0.00765 -0.1306 0.2997 1.0000
8.750 1.5467 0.01352 0.00822 -0.1284 0.2861 1.0000
9.000 1.5584 0.01421 0.00885 -0.1262 0.2719 1.0000
9.250 1.5703 0.01492 0.00951 -0.1241 0.2591 1.0000
9.500 1.5817 0.01570 0.01023 -0.1220 0.2458 1.0000
10.000 1.6038 0.01737 0.01180 -0.1180 0.2186 1.0000
10.250 1.6145 0.01827 0.01265 -0.1160 0.2051 1.0000
10.500 1.6241 0.01926 0.01357 -0.1140 0.1912 1.0000
10.750 1.6347 0.02022 0.01449 -0.1121 0.1793 1.0000
11.000 1.6442 0.02127 0.01549 -0.1102 0.1676 1.0000
11.250 1.6540 0.02233 0.01651 -0.1084 0.1577 1.0000
11.500 1.6644 0.02337 0.01753 -0.1067 0.1485 1.0000
11.750 1.6746 0.02444 0.01858 -0.1050 0.1398 1.0000
12.000 1.6837 0.02561 0.01973 -0.1033 0.1312 1.0000
12.250 1.6917 0.02688 0.02097 -0.1016 0.1225 1.0000
12.500 1.7013 0.02807 0.02215 -0.1001 0.1146 1.0000
12.750 1.7090 0.02943 0.02350 -0.0984 0.1073 1.0000
13.000 1.7161 0.03088 0.02492 -0.0968 0.0996 1.0000
13.250 1.7245 0.03226 0.02631 -0.0954 0.0935 1.0000
13.500 1.7326 0.03371 0.02776 -0.0941 0.0879 1.0000
13.750 1.7388 0.03535 0.02941 -0.0927 0.0820 1.0000
14.000 1.7466 0.03691 0.03097 -0.0914 0.0764 1.0000
14.250 1.7521 0.03870 0.03277 -0.0901 0.0711 1.0000
14.500 1.7574 0.04056 0.03463 -0.0889 0.0657 1.0000
14.750 1.7628 0.04246 0.03656 -0.0878 0.0607 1.0000
15.000 1.7676 0.04447 0.03857 -0.0867 0.0557 1.0000
15.250 1.7706 0.04671 0.04083 -0.0857 0.0512 1.0000
15.500 1.7734 0.04902 0.04315 -0.0847 0.0468 1.0000
15.750 1.7766 0.05135 0.04551 -0.0839 0.0428 1.0000
16.000 1.7784 0.05390 0.04809 -0.0831 0.0391 1.0000
16.250 1.7800 0.05653 0.05075 -0.0825 0.0360 1.0000
16.500 1.7803 0.05935 0.05361 -0.0819 0.0328 1.0000
16.750 1.7813 0.06219 0.05650 -0.0815 0.0302 1.0000
17.000 1.7810 0.06524 0.05959 -0.0812 0.0277 1.0000
17.250 1.7803 0.06841 0.06281 -0.0810 0.0255 1.0000
17.500 1.7794 0.07168 0.06615 -0.0809 0.0235 1.0000
17.750 1.7760 0.07536 0.06988 -0.0810 0.0217 1.0000
18.000 1.7747 0.07881 0.07341 -0.0812 0.0199 1.0000
18.250 1.7708 0.08270 0.07736 -0.0815 0.0184 1.0000
18.500 1.7669 0.08669 0.08142 -0.0821 0.0170 1.0000
18.750 1.7609 0.09103 0.08584 -0.0828 0.0156 1.0000
19.000 1.7563 0.09526 0.09016 -0.0836 0.0146 1.0000
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Polar data table (+)
Polar graphs
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