GOE 532 AIRFOIL (goe532-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 532 AIRFOIL (goe532-il) Reynolds number: 100,000 Max Cl/Cd: 53.3 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe532-il-100000.txt Download as CSV file: xf-goe532-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 532 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2610 0.10154 0.09658 -0.0331 1.0000 0.1155
-8.750 -0.2832 0.10076 0.09594 -0.0356 1.0000 0.1196
-8.500 -0.3238 0.10110 0.09650 -0.0367 1.0000 0.1204
-8.250 -0.2752 0.09449 0.08982 -0.0331 1.0000 0.1235
-8.000 -0.2690 0.09235 0.08775 -0.0312 1.0000 0.1265
-7.750 -0.2766 0.09089 0.08640 -0.0293 1.0000 0.1300
-7.500 -0.3014 0.09045 0.08611 -0.0263 1.0000 0.1327
-7.250 -0.3353 0.09069 0.08652 -0.0221 1.0000 0.1336
-6.750 -0.3393 0.08535 0.08134 -0.0247 0.9936 0.1390
-6.500 -0.3053 0.07870 0.07460 -0.0448 0.9767 0.1526
-6.250 -0.2687 0.07642 0.07237 -0.0390 0.9726 0.1576
-6.000 -0.2356 0.07097 0.06688 -0.0511 0.9588 0.1714
-5.750 -0.1010 0.05043 0.04647 -0.0702 0.9172 0.2038
-5.500 -0.0648 0.04690 0.04291 -0.0720 0.9089 0.2174
-5.250 -0.0406 0.04344 0.03946 -0.0719 0.8949 0.2271
-5.000 -0.0205 0.03991 0.03588 -0.0747 0.8791 0.2435
-4.750 -0.0056 0.03641 0.03220 -0.0817 0.8598 0.2734
-4.500 0.0007 0.03259 0.02605 -0.1043 0.8860 0.1162
-4.250 0.0408 0.02892 0.02150 -0.1065 0.8738 0.1044
-4.000 0.0732 0.02678 0.01904 -0.1070 0.8580 0.1023
-3.750 0.1049 0.02522 0.01714 -0.1072 0.8418 0.1025
-3.500 0.1355 0.02394 0.01554 -0.1069 0.8257 0.1032
-3.250 0.1652 0.02279 0.01413 -0.1065 0.8101 0.1032
-3.000 0.1945 0.02184 0.01296 -0.1060 0.7953 0.1039
-2.750 0.2240 0.02103 0.01194 -0.1054 0.7817 0.1052
-2.500 0.2501 0.02022 0.01111 -0.1045 0.7666 0.1086
-2.250 0.2756 0.01966 0.01059 -0.1036 0.7522 0.1136
-2.000 0.3022 0.01922 0.01009 -0.1028 0.7397 0.1187
-1.750 0.3295 0.01866 0.00952 -0.1021 0.7295 0.1256
-1.500 0.3543 0.01836 0.00926 -0.1013 0.7173 0.1385
-1.250 0.3808 0.01779 0.00891 -0.1007 0.7077 0.1807
-1.000 0.4005 0.01655 0.00914 -0.0989 0.6981 0.5594
-0.750 0.4210 0.01640 0.00931 -0.0964 0.6889 0.6888
-0.500 0.4417 0.01604 0.00926 -0.0936 0.6800 0.8113
-0.250 0.4941 0.01585 0.00904 -0.0978 0.6692 1.0000
0.000 0.5230 0.01606 0.00894 -0.0979 0.6607 1.0000
0.250 0.5489 0.01639 0.00909 -0.0976 0.6512 1.0000
0.500 0.5772 0.01661 0.00906 -0.0973 0.6430 1.0000
0.750 0.6025 0.01697 0.00931 -0.0969 0.6341 1.0000
1.000 0.6300 0.01726 0.00942 -0.0966 0.6268 1.0000
1.250 0.6566 0.01764 0.00968 -0.0963 0.6200 1.0000
1.500 0.6823 0.01799 0.00995 -0.0959 0.6120 1.0000
1.750 0.7112 0.01826 0.01001 -0.0957 0.6056 1.0000
2.000 0.7344 0.01869 0.01047 -0.0950 0.5969 1.0000
2.250 0.7623 0.01895 0.01058 -0.0946 0.5899 1.0000
2.500 0.7866 0.01933 0.01094 -0.0939 0.5812 1.0000
2.750 0.8136 0.01954 0.01103 -0.0934 0.5729 1.0000
3.000 0.8384 0.01988 0.01135 -0.0927 0.5646 1.0000
3.250 0.8643 0.02019 0.01162 -0.0922 0.5570 1.0000
3.500 0.8921 0.02050 0.01182 -0.0919 0.5510 1.0000
3.750 0.9147 0.02094 0.01235 -0.0911 0.5426 1.0000
4.000 0.9428 0.02115 0.01245 -0.0907 0.5359 1.0000
4.250 0.9655 0.02159 0.01298 -0.0899 0.5274 1.0000
4.500 0.9925 0.02179 0.01311 -0.0894 0.5196 1.0000
4.750 1.0160 0.02215 0.01351 -0.0885 0.5106 1.0000
5.000 1.0430 0.02223 0.01354 -0.0879 0.5015 1.0000
5.250 1.0655 0.02250 0.01386 -0.0869 0.4902 1.0000
5.500 1.0925 0.02250 0.01376 -0.0862 0.4798 1.0000
5.750 1.1162 0.02255 0.01382 -0.0851 0.4671 1.0000
6.000 1.1382 0.02269 0.01399 -0.0839 0.4534 1.0000
6.250 1.1611 0.02277 0.01406 -0.0827 0.4392 1.0000
6.500 1.1837 0.02283 0.01410 -0.0815 0.4240 1.0000
6.750 1.2053 0.02294 0.01417 -0.0801 0.4078 1.0000
7.000 1.2257 0.02312 0.01432 -0.0786 0.3910 1.0000
7.250 1.2460 0.02340 0.01459 -0.0772 0.3750 1.0000
7.500 1.2664 0.02376 0.01488 -0.0759 0.3606 1.0000
7.750 1.2870 0.02415 0.01521 -0.0746 0.3478 1.0000
8.000 1.3055 0.02472 0.01583 -0.0732 0.3355 1.0000
8.250 1.3252 0.02530 0.01644 -0.0720 0.3253 1.0000
8.500 1.3464 0.02579 0.01684 -0.0709 0.3167 1.0000
8.750 1.3639 0.02648 0.01764 -0.0695 0.3072 1.0000
9.000 1.3834 0.02704 0.01814 -0.0683 0.2989 1.0000
9.250 1.3997 0.02771 0.01888 -0.0667 0.2899 1.0000
9.500 1.4182 0.02841 0.01957 -0.0655 0.2824 1.0000
9.750 1.4343 0.02916 0.02038 -0.0639 0.2744 1.0000
10.000 1.4502 0.02996 0.02119 -0.0624 0.2664 1.0000
10.250 1.4648 0.03076 0.02201 -0.0607 0.2580 1.0000
10.500 1.4768 0.03173 0.02304 -0.0588 0.2495 1.0000
10.750 1.4936 0.03263 0.02381 -0.0575 0.2401 1.0000
11.000 1.4956 0.03376 0.02514 -0.0543 0.2314 1.0000
11.250 1.5059 0.03496 0.02627 -0.0523 0.2212 1.0000
11.500 1.5134 0.03622 0.02748 -0.0501 0.2104 1.0000
11.750 1.5120 0.03788 0.02926 -0.0471 0.2004 1.0000
12.000 1.5208 0.03954 0.03085 -0.0454 0.1900 1.0000
12.250 1.5278 0.04117 0.03247 -0.0436 0.1810 1.0000
12.500 1.5331 0.04317 0.03457 -0.0419 0.1737 1.0000
12.750 1.5392 0.04493 0.03639 -0.0402 0.1674 1.0000
13.000 1.5567 0.04664 0.03805 -0.0396 0.1614 1.0000
13.250 1.5485 0.04902 0.04071 -0.0374 0.1576 1.0000
13.500 1.5519 0.05100 0.04281 -0.0360 0.1534 1.0000
13.750 1.5840 0.05217 0.04379 -0.0363 0.1485 1.0000
14.000 1.5692 0.05516 0.04712 -0.0343 0.1465 1.0000
14.250 1.5564 0.05841 0.05066 -0.0329 0.1441 1.0000
14.500 1.5473 0.06162 0.05409 -0.0320 0.1417 1.0000
14.750 1.5454 0.06438 0.05698 -0.0315 0.1391 1.0000
15.000 1.5823 0.06457 0.05697 -0.0312 0.1353 1.0000
15.250 1.5555 0.06944 0.06220 -0.0308 0.1343 1.0000
15.500 1.5250 0.07528 0.06837 -0.0314 0.1334 1.0000
15.750 1.4874 0.08256 0.07598 -0.0332 0.1328 1.0000
16.000 1.4327 0.09294 0.08669 -0.0371 0.1327 1.0000
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Polar data table (+)
Polar graphs
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