GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 711 AIRFOIL (goe711-il) Reynolds number: 200,000 Max Cl/Cd: 62.88 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe711-il-200000-n5.txt Download as CSV file: xf-goe711-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 711 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 -0.0701 0.09406 0.09050 -0.0942 0.9551 0.0329
-8.500 -0.0655 0.08942 0.08587 -0.0999 0.9494 0.0331
-8.250 -0.0626 0.08533 0.08179 -0.1034 0.9427 0.0332
-7.750 -0.0522 0.07635 0.07279 -0.1120 0.9283 0.0333
-7.250 -0.0304 0.07054 0.06697 -0.1120 0.9170 0.0344
-7.000 -0.0217 0.06858 0.06502 -0.1115 0.9082 0.0357
-6.750 -0.0069 0.06473 0.06109 -0.1157 0.9017 0.0382
-6.500 0.0043 0.05803 0.05404 -0.1238 0.8901 0.0403
-6.250 0.0208 0.05376 0.04959 -0.1258 0.8834 0.0403
-6.000 0.0307 0.05185 0.04785 -0.1236 0.8750 0.0365
-5.750 0.0496 0.04781 0.04361 -0.1258 0.8666 0.0368
-5.500 0.0717 0.04389 0.03944 -0.1277 0.8583 0.0373
-5.250 0.0921 0.03883 0.03398 -0.1290 0.8482 0.0352
-5.000 0.1179 0.03534 0.03015 -0.1302 0.8395 0.0352
-4.750 0.1438 0.03326 0.02783 -0.1308 0.8287 0.0366
-4.500 0.1699 0.03064 0.02487 -0.1313 0.8174 0.0370
-4.250 0.1977 0.02810 0.02194 -0.1318 0.8067 0.0369
-3.750 0.2547 0.02438 0.01745 -0.1324 0.7825 0.0383
-3.500 0.2831 0.02293 0.01564 -0.1326 0.7693 0.0389
-3.250 0.3116 0.02165 0.01402 -0.1327 0.7557 0.0391
-3.000 0.3399 0.02060 0.01266 -0.1327 0.7415 0.0394
-2.750 0.3681 0.01974 0.01150 -0.1327 0.7270 0.0397
-2.500 0.3959 0.01913 0.01060 -0.1325 0.7117 0.0403
-2.250 0.4229 0.01834 0.00965 -0.1325 0.6963 0.0414
-2.000 0.4497 0.01783 0.00901 -0.1323 0.6808 0.0423
-1.750 0.4764 0.01737 0.00839 -0.1321 0.6653 0.0427
-1.500 0.5027 0.01698 0.00787 -0.1318 0.6492 0.0433
-1.250 0.5287 0.01666 0.00742 -0.1315 0.6329 0.0439
-1.000 0.5545 0.01639 0.00704 -0.1311 0.6169 0.0447
-0.750 0.5801 0.01617 0.00672 -0.1307 0.6013 0.0456
-0.500 0.6055 0.01603 0.00647 -0.1303 0.5859 0.0470
0.000 0.6556 0.01583 0.00609 -0.1294 0.5546 0.0501
0.250 0.6805 0.01572 0.00591 -0.1290 0.5396 0.0516
0.500 0.7055 0.01571 0.00581 -0.1287 0.5256 0.0534
0.750 0.7305 0.01574 0.00575 -0.1283 0.5122 0.0558
1.000 0.7551 0.01582 0.00571 -0.1278 0.4990 0.0587
1.250 0.7795 0.01590 0.00570 -0.1273 0.4863 0.0649
1.500 0.8038 0.01599 0.00573 -0.1268 0.4739 0.0770
1.750 0.8219 0.01400 0.00601 -0.1249 0.4634 1.0000
2.000 0.8457 0.01426 0.00608 -0.1243 0.4533 1.0000
2.250 0.8695 0.01452 0.00620 -0.1236 0.4430 1.0000
2.500 0.8932 0.01478 0.00633 -0.1231 0.4333 1.0000
3.000 0.9398 0.01534 0.00667 -0.1218 0.4154 1.0000
3.250 0.9621 0.01565 0.00686 -0.1210 0.4077 1.0000
3.500 0.9859 0.01591 0.00706 -0.1204 0.4004 1.0000
3.750 1.0082 0.01622 0.00729 -0.1196 0.3937 1.0000
4.000 1.0312 0.01651 0.00752 -0.1190 0.3873 1.0000
4.250 1.0534 0.01682 0.00777 -0.1182 0.3807 1.0000
4.500 1.0748 0.01716 0.00805 -0.1173 0.3751 1.0000
4.750 1.0973 0.01745 0.00832 -0.1166 0.3692 1.0000
5.000 1.1180 0.01778 0.00861 -0.1155 0.3639 1.0000
5.250 1.1378 0.01816 0.00893 -0.1143 0.3596 1.0000
5.500 1.1596 0.01846 0.00925 -0.1135 0.3550 1.0000
5.750 1.1803 0.01881 0.00960 -0.1125 0.3505 1.0000
6.000 1.1998 0.01923 0.00997 -0.1114 0.3459 1.0000
6.250 1.2200 0.01961 0.01035 -0.1104 0.3411 1.0000
6.500 1.2400 0.01999 0.01075 -0.1093 0.3357 1.0000
6.750 1.2588 0.02043 0.01117 -0.1081 0.3309 1.0000
7.000 1.2781 0.02088 0.01162 -0.1070 0.3266 1.0000
7.250 1.2985 0.02128 0.01206 -0.1062 0.3224 1.0000
7.500 1.3179 0.02172 0.01253 -0.1051 0.3183 1.0000
7.750 1.3361 0.02223 0.01304 -0.1040 0.3144 1.0000
8.000 1.3549 0.02272 0.01356 -0.1029 0.3106 1.0000
8.250 1.3742 0.02318 0.01408 -0.1020 0.3064 1.0000
8.500 1.3922 0.02369 0.01464 -0.1008 0.3024 1.0000
8.750 1.4090 0.02428 0.01524 -0.0996 0.2987 1.0000
9.000 1.4265 0.02485 0.01586 -0.0984 0.2949 1.0000
9.250 1.4436 0.02540 0.01650 -0.0973 0.2897 1.0000
9.500 1.4571 0.02611 0.01722 -0.0957 0.2836 1.0000
9.750 1.4713 0.02681 0.01799 -0.0942 0.2770 1.0000
10.000 1.4844 0.02758 0.01880 -0.0926 0.2697 1.0000
10.250 1.4970 0.02842 0.01968 -0.0911 0.2637 1.0000
10.500 1.5110 0.02921 0.02055 -0.0898 0.2568 1.0000
10.750 1.5207 0.03027 0.02163 -0.0880 0.2504 1.0000
11.000 1.5334 0.03119 0.02264 -0.0867 0.2414 1.0000
11.250 1.5419 0.03240 0.02387 -0.0850 0.2320 1.0000
11.500 1.5491 0.03377 0.02525 -0.0832 0.2215 1.0000
11.750 1.5560 0.03522 0.02672 -0.0816 0.2091 1.0000
12.000 1.5593 0.03699 0.02850 -0.0798 0.1948 1.0000
12.250 1.5591 0.03913 0.03061 -0.0778 0.1778 1.0000
12.500 1.5525 0.04198 0.03337 -0.0756 0.1550 1.0000
12.750 1.5395 0.04562 0.03690 -0.0733 0.1323 1.0000
13.000 1.5240 0.04973 0.04094 -0.0713 0.1135 1.0000
13.250 1.5056 0.05443 0.04559 -0.0696 0.0722 1.0000
13.500 1.4814 0.06007 0.05118 -0.0683 0.0595 1.0000
13.750 1.4673 0.06483 0.05603 -0.0677 0.0529 1.0000
14.000 1.4572 0.06927 0.06062 -0.0674 0.0479 1.0000
14.250 1.4505 0.07342 0.06491 -0.0674 0.0424 1.0000
14.750 1.4270 0.08333 0.07503 -0.0679 0.0239 1.0000
15.000 1.4135 0.08872 0.08050 -0.0685 0.0219 1.0000
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Polar data table (+)
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