GOE 509 AIRFOIL (goe509-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 509 AIRFOIL (goe509-il) Reynolds number: 200,000 Max Cl/Cd: 68.84 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe509-il-200000-n5.txt Download as CSV file: xf-goe509-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 509 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2959 0.12057 0.11705 -0.0327 1.0000 0.0266
-10.500 -0.2959 0.11777 0.11428 -0.0326 1.0000 0.0261
-10.000 -0.3127 0.10760 0.10417 -0.0351 0.9995 0.0188
-9.750 -0.2975 0.10374 0.10031 -0.0384 0.9969 0.0186
-9.500 -0.2861 0.09922 0.09580 -0.0425 0.9937 0.0185
-9.250 -0.2766 0.09464 0.09122 -0.0466 0.9899 0.0185
-9.000 -0.2666 0.08966 0.08625 -0.0515 0.9861 0.0185
-8.750 -0.2635 0.08355 0.08015 -0.0573 0.9803 0.0188
-8.500 -0.2501 0.07952 0.07613 -0.0623 0.9755 0.0191
-8.250 -0.2304 0.07832 0.07494 -0.0641 0.9702 0.0205
-8.000 -0.2257 0.07236 0.06897 -0.0712 0.9628 0.0200
-7.750 -0.2189 0.06800 0.06460 -0.0749 0.9529 0.0204
-7.500 -0.2110 0.06294 0.05949 -0.0792 0.9437 0.0208
-7.250 -0.1994 0.05664 0.05307 -0.0845 0.9352 0.0210
-7.000 -0.1977 0.05100 0.04731 -0.0860 0.9205 0.0212
-6.750 -0.2081 0.04511 0.04124 -0.0839 0.8968 0.0216
-6.500 -0.2401 0.02781 0.02244 -0.0812 0.8786 0.0237
-6.250 -0.2136 0.02713 0.02169 -0.0813 0.8688 0.0245
-6.000 -0.1879 0.02513 0.01933 -0.0815 0.8611 0.0257
-5.750 -0.1633 0.02248 0.01608 -0.0811 0.8526 0.0276
-5.500 -0.1335 0.02098 0.01422 -0.0817 0.8441 0.0297
-5.250 -0.0991 0.02023 0.01329 -0.0831 0.8359 0.0315
-5.000 -0.0686 0.01906 0.01179 -0.0835 0.8267 0.0336
-4.500 -0.0073 0.01755 0.00988 -0.0845 0.8088 0.0382
-4.250 0.0223 0.01696 0.00910 -0.0847 0.7986 0.0406
-4.000 0.0512 0.01648 0.00837 -0.0847 0.7885 0.0432
-3.750 0.0772 0.01579 0.00758 -0.0842 0.7782 0.0452
-3.500 0.1042 0.01542 0.00714 -0.0840 0.7681 0.0476
-3.250 0.1297 0.01509 0.00672 -0.0833 0.7583 0.0504
-3.000 0.1556 0.01471 0.00623 -0.0827 0.7496 0.0526
-2.750 0.1808 0.01433 0.00577 -0.0820 0.7403 0.0549
-2.500 0.2050 0.01399 0.00544 -0.0812 0.7307 0.0584
-2.250 0.2301 0.01375 0.00513 -0.0804 0.7208 0.0617
-2.000 0.2536 0.01354 0.00484 -0.0793 0.7093 0.0649
-1.750 0.2772 0.01329 0.00457 -0.0783 0.6981 0.0694
-1.500 0.3013 0.01313 0.00435 -0.0774 0.6865 0.0765
-1.250 0.3248 0.01296 0.00415 -0.0763 0.6740 0.0851
-1.000 0.3480 0.01279 0.00396 -0.0752 0.6604 0.0985
-0.750 0.3703 0.01257 0.00380 -0.0739 0.6454 0.1277
-0.500 0.3906 0.01229 0.00383 -0.0724 0.6285 0.2279
-0.250 0.4128 0.01231 0.00382 -0.0711 0.6093 0.2714
0.000 0.4345 0.01234 0.00380 -0.0697 0.5884 0.2975
0.250 0.4556 0.01240 0.00377 -0.0682 0.5655 0.3201
0.500 0.4751 0.01246 0.00375 -0.0664 0.5403 0.3403
0.750 0.4936 0.01254 0.00373 -0.0644 0.5153 0.3613
1.000 0.5114 0.01261 0.00373 -0.0623 0.4942 0.3873
1.250 0.5290 0.01261 0.00374 -0.0602 0.4796 0.4264
1.750 0.7044 0.01259 0.00460 -0.0862 0.4492 0.9803
2.000 0.7458 0.01286 0.00476 -0.0893 0.4405 0.9908
2.250 0.7903 0.01312 0.00489 -0.0931 0.4337 0.9984
2.500 0.8188 0.01328 0.00501 -0.0934 0.4280 1.0000
2.750 0.8395 0.01347 0.00514 -0.0920 0.4219 1.0000
3.000 0.8597 0.01371 0.00528 -0.0906 0.4164 1.0000
3.250 0.8810 0.01386 0.00543 -0.0893 0.4104 1.0000
3.500 0.9014 0.01406 0.00559 -0.0878 0.4043 1.0000
3.750 0.9217 0.01430 0.00576 -0.0864 0.3992 1.0000
4.000 0.9431 0.01445 0.00594 -0.0852 0.3945 1.0000
4.250 0.9639 0.01463 0.00613 -0.0839 0.3896 1.0000
4.500 0.9843 0.01486 0.00633 -0.0825 0.3852 1.0000
4.750 1.0051 0.01506 0.00655 -0.0811 0.3808 1.0000
5.000 1.0255 0.01523 0.00676 -0.0797 0.3751 1.0000
5.250 1.0450 0.01545 0.00697 -0.0782 0.3695 1.0000
5.500 1.0643 0.01565 0.00721 -0.0766 0.3629 1.0000
5.750 1.0823 0.01585 0.00742 -0.0747 0.3541 1.0000
6.000 1.1002 0.01605 0.00764 -0.0729 0.3451 1.0000
6.250 1.1172 0.01628 0.00787 -0.0709 0.3361 1.0000
6.500 1.1352 0.01649 0.00814 -0.0690 0.3269 1.0000
6.750 1.1515 0.01675 0.00840 -0.0669 0.3185 1.0000
7.000 1.1687 0.01699 0.00869 -0.0650 0.3084 1.0000
7.250 1.1833 0.01728 0.00898 -0.0626 0.2966 1.0000
7.500 1.1950 0.01759 0.00928 -0.0597 0.2839 1.0000
7.750 1.2043 0.01797 0.00961 -0.0563 0.2682 1.0000
8.000 1.2128 0.01843 0.01001 -0.0529 0.2518 1.0000
8.250 1.2223 0.01893 0.01046 -0.0499 0.2384 1.0000
8.500 1.2322 0.01947 0.01098 -0.0470 0.2270 1.0000
8.750 1.2423 0.02005 0.01155 -0.0442 0.2178 1.0000
9.000 1.2542 0.02060 0.01211 -0.0418 0.2098 1.0000
9.250 1.2645 0.02123 0.01275 -0.0392 0.2031 1.0000
9.500 1.2768 0.02181 0.01338 -0.0370 0.1968 1.0000
9.750 1.2863 0.02254 0.01412 -0.0345 0.1904 1.0000
10.000 1.2982 0.02319 0.01484 -0.0324 0.1855 1.0000
10.250 1.3096 0.02388 0.01559 -0.0303 0.1803 1.0000
10.500 1.3188 0.02472 0.01646 -0.0280 0.1751 1.0000
10.750 1.3295 0.02551 0.01732 -0.0261 0.1691 1.0000
11.000 1.3388 0.02640 0.01827 -0.0241 0.1626 1.0000
11.250 1.3465 0.02744 0.01936 -0.0220 0.1563 1.0000
11.500 1.3571 0.02834 0.02037 -0.0203 0.1484 1.0000
11.750 1.3650 0.02946 0.02154 -0.0186 0.1393 1.0000
12.000 1.3708 0.03078 0.02287 -0.0168 0.1182 1.0000
12.250 1.3603 0.03340 0.02522 -0.0141 0.0866 1.0000
12.500 1.3534 0.03594 0.02771 -0.0120 0.0719 1.0000
13.000 1.3344 0.04195 0.03362 -0.0085 0.0411 1.0000
13.250 1.3289 0.04482 0.03657 -0.0074 0.0380 1.0000
13.500 1.3266 0.04751 0.03939 -0.0066 0.0364 1.0000
13.750 1.3214 0.05063 0.04265 -0.0060 0.0348 1.0000
14.000 1.3144 0.05408 0.04624 -0.0057 0.0335 1.0000
14.250 1.3045 0.05806 0.05035 -0.0057 0.0323 1.0000
14.500 1.2927 0.06250 0.05494 -0.0060 0.0314 1.0000
14.750 1.2863 0.06639 0.05898 -0.0065 0.0306 1.0000
15.000 1.2784 0.07065 0.06340 -0.0072 0.0297 1.0000
15.250 1.2694 0.07518 0.06807 -0.0082 0.0289 1.0000
15.500 1.2588 0.08003 0.07308 -0.0093 0.0282 1.0000
15.750 1.2477 0.08503 0.07820 -0.0105 0.0275 1.0000
16.000 1.2354 0.09027 0.08357 -0.0120 0.0270 1.0000
16.250 1.2222 0.09568 0.08909 -0.0135 0.0262 1.0000
16.500 1.2095 0.10104 0.09455 -0.0151 0.0258 1.0000
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