GOE 335 (D.F.W.) AIRFOIL (goe335-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 335 (D.F.W.) AIRFOIL (goe335-il) Reynolds number: 50,000 Max Cl/Cd: 41.14 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe335-il-50000-n5.txt Download as CSV file: xf-goe335-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 335 (D.F.W.) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3134 0.10045 0.09405 -0.0257 1.0000 0.0777
-7.250 -0.3192 0.09954 0.09329 -0.0275 1.0000 0.0791
-7.000 -0.3202 0.09830 0.09216 -0.0305 1.0000 0.0797
-6.750 -0.3162 0.09423 0.08819 -0.0296 1.0000 0.0809
-6.500 -0.3099 0.09013 0.08415 -0.0264 1.0000 0.0835
-6.250 -0.3072 0.08751 0.08161 -0.0259 1.0000 0.0862
-6.000 -0.3054 0.08525 0.07942 -0.0265 1.0000 0.0895
-5.750 -0.3024 0.08400 0.07823 -0.0306 1.0000 0.0933
-5.500 -0.2951 0.08247 0.07670 -0.0352 1.0000 0.0943
-5.250 -0.2967 0.07820 0.07256 -0.0304 1.0000 0.0959
-5.000 -0.2950 0.07540 0.06982 -0.0281 1.0000 0.0987
-4.750 -0.2897 0.07309 0.06752 -0.0283 1.0000 0.1036
-4.250 -0.2703 0.06765 0.06206 -0.0306 0.9991 0.1162
-4.000 -0.2328 0.06342 0.05765 -0.0381 0.9915 0.1268
-3.500 -0.1388 0.05241 0.04594 -0.0538 0.9782 0.0749
-3.250 -0.0988 0.04840 0.04161 -0.0592 0.9708 0.0750
-3.000 -0.0542 0.04391 0.03668 -0.0648 0.9641 0.0704
-2.750 -0.0089 0.03987 0.03208 -0.0697 0.9556 0.0689
-2.500 0.0329 0.03715 0.02891 -0.0734 0.9445 0.0754
-2.250 0.0786 0.03398 0.02513 -0.0772 0.9333 0.0751
-2.000 0.1242 0.03128 0.02178 -0.0804 0.9219 0.0760
-1.750 0.1679 0.02940 0.01946 -0.0834 0.9110 0.0840
-1.500 0.2049 0.02778 0.01739 -0.0848 0.8995 0.0857
-1.250 0.2430 0.02638 0.01557 -0.0863 0.8890 0.0866
-1.000 0.2819 0.02515 0.01397 -0.0877 0.8792 0.0884
-0.750 0.3233 0.02409 0.01252 -0.0893 0.8697 0.0911
-0.500 0.3589 0.02327 0.01145 -0.0901 0.8579 0.0949
-0.250 0.3936 0.02253 0.01062 -0.0908 0.8457 0.1020
0.000 0.4275 0.02191 0.00990 -0.0914 0.8331 0.1168
0.250 0.4605 0.02123 0.00936 -0.0920 0.8197 0.1575
0.500 0.4972 0.01870 0.00879 -0.0932 0.8068 1.0000
0.750 0.5277 0.01877 0.00844 -0.0930 0.7912 1.0000
1.000 0.5570 0.01885 0.00824 -0.0926 0.7745 1.0000
1.250 0.5854 0.01894 0.00811 -0.0921 0.7573 1.0000
1.500 0.6113 0.01910 0.00809 -0.0913 0.7384 1.0000
1.750 0.6369 0.01925 0.00809 -0.0904 0.7182 1.0000
2.000 0.6636 0.01937 0.00806 -0.0896 0.6988 1.0000
2.250 0.6882 0.01957 0.00816 -0.0886 0.6771 1.0000
2.500 0.7142 0.01974 0.00820 -0.0878 0.6567 1.0000
2.750 0.7393 0.01997 0.00833 -0.0869 0.6356 1.0000
3.000 0.7647 0.02022 0.00849 -0.0861 0.6155 1.0000
3.250 0.7906 0.02049 0.00868 -0.0854 0.5974 1.0000
3.500 0.8154 0.02086 0.00898 -0.0847 0.5790 1.0000
3.750 0.8405 0.02124 0.00931 -0.0841 0.5624 1.0000
4.000 0.8659 0.02165 0.00973 -0.0835 0.5476 1.0000
4.250 0.8913 0.02209 0.01016 -0.0830 0.5341 1.0000
4.500 0.9168 0.02255 0.01062 -0.0825 0.5219 1.0000
4.750 0.9427 0.02303 0.01116 -0.0821 0.5108 1.0000
5.000 0.9674 0.02359 0.01182 -0.0816 0.4996 1.0000
5.250 0.9923 0.02418 0.01250 -0.0811 0.4895 1.0000
5.500 1.0179 0.02474 0.01313 -0.0807 0.4802 1.0000
5.750 1.0422 0.02536 0.01394 -0.0801 0.4699 1.0000
6.000 1.0657 0.02602 0.01475 -0.0794 0.4592 1.0000
6.250 1.0899 0.02666 0.01554 -0.0788 0.4491 1.0000
6.500 1.1144 0.02732 0.01636 -0.0782 0.4397 1.0000
6.750 1.1367 0.02814 0.01752 -0.0774 0.4302 1.0000
7.000 1.1613 0.02889 0.01850 -0.0769 0.4220 1.0000
7.250 1.1838 0.02964 0.01951 -0.0759 0.4112 1.0000
7.500 1.1988 0.02997 0.02000 -0.0736 0.3873 1.0000
7.750 1.2121 0.03019 0.02032 -0.0709 0.3610 1.0000
8.000 1.2253 0.03056 0.02088 -0.0685 0.3377 1.0000
8.250 1.2314 0.03098 0.02155 -0.0651 0.3049 1.0000
8.500 1.2313 0.03168 0.02233 -0.0614 0.2467 1.0000
8.750 1.2246 0.03355 0.02347 -0.0574 0.1481 1.0000
9.000 1.2108 0.03699 0.02614 -0.0538 0.0805 1.0000
9.500 1.1973 0.04285 0.03203 -0.0483 0.0530 1.0000
9.750 1.1899 0.04596 0.03521 -0.0465 0.0478 1.0000
10.000 1.1843 0.04911 0.03854 -0.0453 0.0442 1.0000
10.250 1.1762 0.05276 0.04232 -0.0448 0.0414 1.0000
10.500 1.1672 0.05677 0.04642 -0.0447 0.0398 1.0000
10.750 1.1610 0.06068 0.05056 -0.0448 0.0381 1.0000
11.000 1.1551 0.06470 0.05477 -0.0451 0.0369 1.0000
11.250 1.1503 0.06869 0.05892 -0.0455 0.0358 1.0000
11.500 1.1467 0.07257 0.06295 -0.0458 0.0348 1.0000
11.750 1.1441 0.07636 0.06685 -0.0461 0.0337 1.0000
12.000 1.1425 0.07997 0.07054 -0.0462 0.0326 1.0000
12.250 1.1445 0.08312 0.07380 -0.0458 0.0313 1.0000
12.500 1.1492 0.08608 0.07703 -0.0452 0.0298 1.0000
12.750 1.1535 0.08922 0.08041 -0.0448 0.0285 1.0000
13.000 1.1583 0.09243 0.08386 -0.0444 0.0276 1.0000
13.250 1.1622 0.09601 0.08769 -0.0443 0.0271 1.0000
13.500 1.1627 0.10030 0.09235 -0.0449 0.0267 1.0000
13.750 1.1595 0.10530 0.09762 -0.0464 0.0265 1.0000
14.000 1.1532 0.11098 0.10355 -0.0486 0.0265 1.0000
14.250 1.1442 0.11737 0.11018 -0.0517 0.0265 1.0000
14.500 1.1330 0.12453 0.11757 -0.0556 0.0267 1.0000
14.750 1.1195 0.13259 0.12585 -0.0603 0.0269 1.0000
15.000 1.1049 0.14146 0.13490 -0.0657 0.0273 1.0000
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Polar data table (+)
Polar graphs
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