GOE 328 AIRFOIL (goe328-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 328 AIRFOIL (goe328-il) Reynolds number: 200,000 Max Cl/Cd: 75.23 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe328-il-200000.txt Download as CSV file: xf-goe328-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 328 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3752 0.10681 0.10322 -0.0158 1.0000 0.0373
-8.500 -0.3756 0.10499 0.10145 -0.0208 1.0000 0.0378
-8.250 -0.3755 0.10270 0.09922 -0.0252 1.0000 0.0380
-8.000 -0.3690 0.09958 0.09613 -0.0310 1.0000 0.0381
-7.750 -0.3631 0.09435 0.09094 -0.0312 1.0000 0.0385
-7.500 -0.3542 0.09026 0.08686 -0.0274 1.0000 0.0390
-7.250 -0.3450 0.08707 0.08369 -0.0266 1.0000 0.0397
-7.000 -0.3370 0.08417 0.08083 -0.0273 1.0000 0.0406
-6.750 -0.3309 0.08144 0.07814 -0.0286 1.0000 0.0416
-6.500 -0.3302 0.07913 0.07589 -0.0290 1.0000 0.0424
-6.250 -0.3390 0.07763 0.07446 -0.0274 1.0000 0.0429
-6.000 -0.3371 0.07534 0.07219 -0.0286 0.9982 0.0438
-5.750 -0.2723 0.07004 0.06659 -0.0494 0.9900 0.0473
-5.500 -0.2339 0.06364 0.06001 -0.0586 0.9846 0.0480
-5.250 -0.2122 0.05897 0.05539 -0.0603 0.9796 0.0490
-5.000 -0.1818 0.05552 0.05194 -0.0637 0.9742 0.0507
-4.750 -0.1415 0.05174 0.04806 -0.0699 0.9701 0.0534
-4.500 -0.0840 0.04934 0.04510 -0.0792 0.9606 0.0590
-4.250 -0.0520 0.04363 0.03927 -0.0838 0.9542 0.0604
-4.000 -0.0270 0.04055 0.03623 -0.0853 0.9436 0.0618
-3.750 -0.0005 0.03825 0.03387 -0.0865 0.9323 0.0640
-3.500 0.0283 0.03613 0.03157 -0.0878 0.9217 0.0681
-3.250 0.0611 0.03372 0.02871 -0.0894 0.9110 0.0746
-3.000 0.0826 0.03170 0.02671 -0.0893 0.8991 0.0769
-2.750 0.1074 0.03013 0.02501 -0.0892 0.8881 0.0810
-2.500 0.1372 0.02856 0.02299 -0.0894 0.8785 0.0894
-2.250 0.1604 0.02679 0.02124 -0.0893 0.8669 0.0927
-2.000 0.1891 0.02577 0.01986 -0.0893 0.8563 0.1042
-1.750 0.2131 0.02413 0.01822 -0.0891 0.8466 0.1091
-1.500 0.2402 0.02292 0.01682 -0.0891 0.8356 0.1219
-1.250 0.2667 0.02182 0.01560 -0.0891 0.8251 0.1371
-1.000 0.2925 0.02103 0.01465 -0.0889 0.8154 0.1650
-0.250 0.3888 0.01701 0.00926 -0.0861 0.7844 0.0737
0.000 0.4161 0.01588 0.00804 -0.0856 0.7719 0.0703
0.250 0.4435 0.01505 0.00708 -0.0850 0.7580 0.0685
0.500 0.4708 0.01443 0.00636 -0.0844 0.7441 0.0682
0.750 0.4982 0.01406 0.00591 -0.0839 0.7307 0.0707
1.000 0.5255 0.01364 0.00544 -0.0835 0.7180 0.0715
1.250 0.5529 0.01327 0.00504 -0.0831 0.7051 0.0723
1.500 0.5802 0.01285 0.00461 -0.0827 0.6919 0.0744
1.750 0.6077 0.01257 0.00433 -0.0825 0.6775 0.0791
2.000 0.6352 0.01246 0.00416 -0.0822 0.6619 0.0873
2.250 0.6629 0.01220 0.00399 -0.0820 0.6452 0.1268
2.500 0.6837 0.01035 0.00387 -0.0802 0.6288 1.0000
2.750 0.7108 0.01050 0.00387 -0.0798 0.6102 1.0000
3.000 0.7377 0.01067 0.00391 -0.0795 0.5916 1.0000
3.250 0.7646 0.01087 0.00396 -0.0793 0.5733 1.0000
3.500 0.7915 0.01107 0.00407 -0.0790 0.5546 1.0000
3.750 0.8184 0.01128 0.00420 -0.0788 0.5362 1.0000
4.000 0.8451 0.01153 0.00436 -0.0786 0.5190 1.0000
4.250 0.8717 0.01180 0.00454 -0.0783 0.5028 1.0000
4.500 0.8983 0.01210 0.00477 -0.0781 0.4877 1.0000
4.750 0.9247 0.01243 0.00503 -0.0779 0.4735 1.0000
5.000 0.9511 0.01278 0.00532 -0.0777 0.4600 1.0000
5.250 0.9773 0.01316 0.00565 -0.0774 0.4472 1.0000
5.500 1.0035 0.01358 0.00601 -0.0772 0.4351 1.0000
5.750 1.0293 0.01398 0.00635 -0.0769 0.4217 1.0000
6.000 1.0548 0.01433 0.00669 -0.0766 0.4071 1.0000
6.250 1.0801 0.01464 0.00704 -0.0763 0.3925 1.0000
6.500 1.1049 0.01494 0.00732 -0.0758 0.3761 1.0000
6.750 1.1295 0.01515 0.00759 -0.0754 0.3581 1.0000
7.000 1.1543 0.01541 0.00790 -0.0750 0.3419 1.0000
7.250 1.1788 0.01567 0.00824 -0.0745 0.3238 1.0000
7.500 1.2021 0.01599 0.00855 -0.0739 0.2984 1.0000
7.750 1.2232 0.01655 0.00899 -0.0730 0.2549 1.0000
8.000 1.2233 0.01970 0.01092 -0.0700 0.0789 1.0000
8.250 1.2350 0.02153 0.01262 -0.0679 0.0573 1.0000
8.500 1.2496 0.02283 0.01405 -0.0662 0.0505 1.0000
8.750 1.2579 0.02455 0.01584 -0.0637 0.0466 1.0000
9.000 1.2710 0.02577 0.01717 -0.0617 0.0436 1.0000
9.250 1.2813 0.02713 0.01857 -0.0596 0.0408 1.0000
9.500 1.2847 0.02893 0.02037 -0.0566 0.0388 1.0000
9.750 1.2893 0.03074 0.02224 -0.0537 0.0375 1.0000
10.000 1.2999 0.03214 0.02375 -0.0516 0.0364 1.0000
10.250 1.3113 0.03369 0.02538 -0.0496 0.0352 1.0000
10.500 1.3241 0.03528 0.02705 -0.0480 0.0340 1.0000
10.750 1.3365 0.03687 0.02870 -0.0464 0.0327 1.0000
11.000 1.3502 0.03866 0.03048 -0.0451 0.0313 1.0000
11.250 1.3812 0.04185 0.03370 -0.0454 0.0300 1.0000
11.500 1.3939 0.04375 0.03582 -0.0438 0.0296 1.0000
11.750 1.4068 0.04603 0.03833 -0.0423 0.0293 1.0000
12.000 1.4176 0.04864 0.04119 -0.0407 0.0290 1.0000
12.250 1.4243 0.05148 0.04430 -0.0389 0.0289 1.0000
12.500 1.4251 0.05433 0.04742 -0.0368 0.0287 1.0000
12.750 1.4218 0.05728 0.05063 -0.0348 0.0284 1.0000
13.000 1.4156 0.06044 0.05406 -0.0330 0.0282 1.0000
13.250 1.4067 0.06390 0.05778 -0.0315 0.0280 1.0000
13.500 1.3956 0.06784 0.06197 -0.0305 0.0280 1.0000
13.750 1.3817 0.07218 0.06656 -0.0299 0.0281 1.0000
14.000 1.3660 0.07703 0.07166 -0.0300 0.0283 1.0000
14.250 1.3488 0.08223 0.07708 -0.0306 0.0286 1.0000
14.500 1.3306 0.08784 0.08290 -0.0318 0.0289 1.0000
14.750 1.3118 0.09383 0.08907 -0.0335 0.0292 1.0000
15.000 1.2935 0.10025 0.09566 -0.0356 0.0295 1.0000
15.250 1.2977 0.10436 0.09987 -0.0357 0.0307 1.0000
15.500 1.2571 0.11320 0.10906 -0.0423 0.0314 1.0000
15.750 1.1787 0.13398 0.13034 -0.0586 0.0334 1.0000
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Polar data table (+)
Polar graphs
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