DAE-11 AIRFOIL (dae11-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: DAE-11 AIRFOIL (dae11-il) Reynolds number: 1,000,000 Max Cl/Cd: 177.31 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-dae11-il-1000000.txt Download as CSV file: xf-dae11-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: DAE-11 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.0465 0.08677 0.08374 -0.0761 0.6799 0.0138
-8.500 -0.0518 0.08168 0.07867 -0.0795 0.6783 0.0147
-8.250 -0.0454 0.07894 0.07592 -0.0807 0.6764 0.0147
-8.000 -0.0429 0.07542 0.07242 -0.0824 0.6748 0.0147
-7.750 -0.0387 0.07277 0.06980 -0.0828 0.6737 0.0151
-7.500 -0.0305 0.07075 0.06780 -0.0834 0.6723 0.0153
-7.250 -0.0273 0.06823 0.06530 -0.0843 0.6707 0.0154
-7.000 -0.0247 0.06612 0.06322 -0.0849 0.6690 0.0156
-6.750 -0.0171 0.06337 0.06048 -0.0873 0.6674 0.0158
-6.500 -0.0080 0.06019 0.05730 -0.0906 0.6657 0.0161
-6.250 0.0034 0.05651 0.05361 -0.0950 0.6642 0.0167
-6.000 0.0197 0.04617 0.04317 -0.1081 0.6625 0.0180
-5.750 0.0313 0.03577 0.03250 -0.1168 0.6607 0.0184
-5.500 0.0533 0.03440 0.03107 -0.1180 0.6590 0.0187
-5.250 0.0689 0.02172 0.01739 -0.1232 0.6579 0.0185
-5.000 0.0907 0.01568 0.01058 -0.1240 0.6566 0.0158
-4.750 0.1180 0.01428 0.00892 -0.1242 0.6551 0.0159
-4.500 0.1459 0.01335 0.00782 -0.1244 0.6534 0.0161
-4.250 0.1740 0.01259 0.00693 -0.1245 0.6516 0.0163
-4.000 0.2024 0.01203 0.00627 -0.1247 0.6499 0.0167
-3.750 0.2309 0.01157 0.00570 -0.1248 0.6483 0.0173
-3.500 0.2594 0.01113 0.00517 -0.1249 0.6466 0.0177
-3.250 0.2880 0.01087 0.00482 -0.1250 0.6443 0.0181
-3.000 0.3160 0.01014 0.00405 -0.1251 0.6429 0.0188
-2.750 0.3448 0.00986 0.00376 -0.1253 0.6413 0.0196
-2.500 0.3737 0.00962 0.00351 -0.1255 0.6396 0.0204
-2.250 0.4026 0.00940 0.00327 -0.1257 0.6376 0.0214
-2.000 0.4314 0.00912 0.00295 -0.1259 0.6357 0.0226
-1.750 0.4603 0.00893 0.00276 -0.1261 0.6338 0.0244
-1.500 0.4893 0.00884 0.00263 -0.1262 0.6319 0.0263
-1.250 0.5181 0.00868 0.00245 -0.1264 0.6295 0.0297
-1.000 0.5471 0.00854 0.00232 -0.1266 0.6276 0.0343
-0.750 0.5761 0.00838 0.00221 -0.1269 0.6256 0.0438
-0.500 0.6050 0.00820 0.00212 -0.1271 0.6233 0.0701
-0.250 0.6337 0.00799 0.00206 -0.1274 0.6210 0.1232
0.000 0.6622 0.00773 0.00203 -0.1277 0.6187 0.2092
0.250 0.6906 0.00750 0.00203 -0.1280 0.6163 0.3112
0.500 0.7186 0.00732 0.00208 -0.1282 0.6136 0.4200
0.750 0.7467 0.00705 0.00213 -0.1284 0.6115 0.5405
1.250 0.8047 0.00610 0.00221 -0.1289 0.6064 1.0000
1.500 0.8335 0.00614 0.00220 -0.1291 0.6036 1.0000
1.750 0.8621 0.00620 0.00220 -0.1293 0.6007 1.0000
2.000 0.8907 0.00627 0.00223 -0.1295 0.5977 1.0000
2.250 0.9195 0.00629 0.00226 -0.1298 0.5947 1.0000
2.500 0.9482 0.00633 0.00228 -0.1300 0.5913 1.0000
2.750 0.9767 0.00638 0.00230 -0.1302 0.5879 1.0000
3.000 1.0049 0.00648 0.00233 -0.1303 0.5843 1.0000
3.250 1.0335 0.00651 0.00239 -0.1306 0.5808 1.0000
3.500 1.0620 0.00656 0.00244 -0.1308 0.5768 1.0000
3.750 1.0902 0.00663 0.00248 -0.1310 0.5726 1.0000
4.000 1.1181 0.00672 0.00255 -0.1311 0.5684 1.0000
4.250 1.1465 0.00678 0.00262 -0.1314 0.5640 1.0000
4.500 1.1744 0.00686 0.00269 -0.1315 0.5591 1.0000
4.750 1.2019 0.00698 0.00278 -0.1316 0.5542 1.0000
5.000 1.2299 0.00705 0.00288 -0.1318 0.5488 1.0000
5.250 1.2573 0.00717 0.00297 -0.1319 0.5428 1.0000
5.500 1.2846 0.00728 0.00309 -0.1320 0.5368 1.0000
5.750 1.3118 0.00740 0.00321 -0.1321 0.5299 1.0000
6.000 1.3385 0.00756 0.00335 -0.1322 0.5232 1.0000
6.250 1.3653 0.00770 0.00350 -0.1322 0.5155 1.0000
6.500 1.3915 0.00788 0.00366 -0.1322 0.5078 1.0000
6.750 1.4175 0.00806 0.00384 -0.1321 0.4987 1.0000
7.000 1.4433 0.00826 0.00403 -0.1320 0.4896 1.0000
7.250 1.4679 0.00851 0.00426 -0.1317 0.4792 1.0000
7.500 1.4923 0.00877 0.00450 -0.1314 0.4676 1.0000
7.750 1.5163 0.00905 0.00476 -0.1311 0.4551 1.0000
8.000 1.5390 0.00938 0.00506 -0.1306 0.4412 1.0000
8.250 1.5603 0.00978 0.00541 -0.1298 0.4256 1.0000
8.500 1.5799 0.01024 0.00581 -0.1288 0.4087 1.0000
8.750 1.5970 0.01079 0.00629 -0.1274 0.3908 1.0000
9.000 1.6129 0.01135 0.00678 -0.1259 0.3727 1.0000
9.250 1.6254 0.01199 0.00736 -0.1238 0.3543 1.0000
9.500 1.6303 0.01270 0.00802 -0.1203 0.3374 1.0000
9.750 1.6297 0.01365 0.00892 -0.1164 0.3219 1.0000
10.000 1.6315 0.01480 0.01003 -0.1134 0.3079 1.0000
10.250 1.6315 0.01626 0.01144 -0.1106 0.2906 1.0000
10.500 1.6329 0.01779 0.01292 -0.1081 0.2747 1.0000
10.750 1.6337 0.01944 0.01451 -0.1058 0.2585 1.0000
11.000 1.6340 0.02118 0.01619 -0.1035 0.2426 1.0000
11.250 1.6342 0.02298 0.01792 -0.1013 0.2269 1.0000
11.500 1.6348 0.02478 0.01967 -0.0992 0.2115 1.0000
11.750 1.6354 0.02663 0.02146 -0.0973 0.1966 1.0000
12.000 1.6360 0.02851 0.02330 -0.0954 0.1831 1.0000
12.250 1.6360 0.03049 0.02523 -0.0936 0.1694 1.0000
12.500 1.6346 0.03261 0.02728 -0.0917 0.1536 1.0000
12.750 1.6360 0.03462 0.02925 -0.0902 0.1420 1.0000
13.000 1.6364 0.03680 0.03138 -0.0887 0.1291 1.0000
13.250 1.6374 0.03896 0.03349 -0.0874 0.1170 1.0000
13.500 1.6381 0.04124 0.03573 -0.0862 0.1059 1.0000
13.750 1.6405 0.04340 0.03787 -0.0851 0.0956 1.0000
14.000 1.6425 0.04568 0.04013 -0.0841 0.0868 1.0000
14.250 1.6442 0.04801 0.04244 -0.0831 0.0778 1.0000
14.500 1.6442 0.05060 0.04500 -0.0823 0.0691 1.0000
14.750 1.6451 0.05313 0.04751 -0.0815 0.0617 1.0000
15.000 1.6475 0.05556 0.04995 -0.0808 0.0554 1.0000
15.250 1.6486 0.05822 0.05261 -0.0802 0.0495 1.0000
15.500 1.6492 0.06095 0.05534 -0.0797 0.0442 1.0000
15.750 1.6516 0.06356 0.05797 -0.0793 0.0401 1.0000
16.000 1.6515 0.06648 0.06090 -0.0790 0.0358 1.0000
16.250 1.6537 0.06921 0.06368 -0.0788 0.0328 1.0000
16.500 1.6535 0.07227 0.06675 -0.0786 0.0295 1.0000
16.750 1.6557 0.07509 0.06963 -0.0786 0.0273 1.0000
17.000 1.6548 0.07833 0.07290 -0.0786 0.0248 1.0000
17.250 1.6563 0.08134 0.07598 -0.0787 0.0230 1.0000
17.500 1.6561 0.08462 0.07930 -0.0789 0.0213 1.0000
17.750 1.6545 0.08815 0.08288 -0.0793 0.0196 1.0000
18.000 1.6555 0.09134 0.08615 -0.0796 0.0185 1.0000
18.250 1.6548 0.09480 0.08966 -0.0801 0.0173 1.0000
18.500 1.6498 0.09898 0.09390 -0.0808 0.0160 1.0000
18.750 1.6510 0.10228 0.09728 -0.0815 0.0152 1.0000
19.000 1.6504 0.10585 0.10092 -0.0823 0.0143 1.0000
19.250 1.6465 0.10998 0.10512 -0.0833 0.0135 1.0000
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Polar data table (+)
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