GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL (goe316-il) Reynolds number: 50,000 Max Cl/Cd: 34.43 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe316-il-50000-n5.txt Download as CSV file: xf-goe316-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 316 (HANSA-BRANDENBURG IV.5) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3692 0.10063 0.09422 -0.0127 1.0000 0.0941
-7.750 -0.3693 0.09813 0.09182 -0.0160 1.0000 0.0978
-7.500 -0.3696 0.09631 0.09005 -0.0256 1.0000 0.1000
-7.250 -0.3567 0.09100 0.08483 -0.0207 1.0000 0.1036
-7.000 -0.3478 0.08779 0.08167 -0.0219 1.0000 0.1099
-6.750 -0.3433 0.08603 0.07986 -0.0334 1.0000 0.1150
-6.500 -0.3323 0.08099 0.07497 -0.0274 1.0000 0.1191
-6.250 -0.3231 0.07801 0.07202 -0.0294 1.0000 0.1259
-6.000 -0.3159 0.07489 0.06892 -0.0332 1.0000 0.1313
-5.750 -0.3090 0.07189 0.06600 -0.0313 1.0000 0.1363
-5.500 -0.3054 0.06977 0.06382 -0.0344 1.0000 0.1457
-5.250 -0.3042 0.06717 0.06137 -0.0308 1.0000 0.1513
-5.000 -0.2965 0.06462 0.05881 -0.0318 0.9967 0.1644
-4.750 -0.2646 0.06083 0.05490 -0.0376 0.9839 0.1932
-4.500 -0.2357 0.05729 0.05132 -0.0409 0.9719 0.2251
-4.250 -0.2077 0.05396 0.04800 -0.0425 0.9606 0.2619
-3.750 -0.0786 0.04373 0.03605 -0.0634 0.9348 0.1090
-3.500 -0.0359 0.04034 0.03213 -0.0667 0.9197 0.0921
-3.250 0.0064 0.03786 0.02893 -0.0691 0.9031 0.0841
-3.000 0.0413 0.03565 0.02634 -0.0705 0.8844 0.0837
-2.750 0.0743 0.03398 0.02420 -0.0710 0.8649 0.0847
-2.500 0.1050 0.03224 0.02213 -0.0711 0.8469 0.0840
-2.250 0.1345 0.03072 0.02029 -0.0710 0.8305 0.0831
-2.000 0.1633 0.02944 0.01869 -0.0706 0.8149 0.0824
-1.750 0.1915 0.02835 0.01729 -0.0700 0.7994 0.0821
-1.500 0.2192 0.02740 0.01606 -0.0693 0.7839 0.0823
-1.250 0.2467 0.02672 0.01506 -0.0685 0.7681 0.0846
-1.000 0.2734 0.02591 0.01407 -0.0677 0.7522 0.0870
-0.750 0.2995 0.02517 0.01319 -0.0666 0.7360 0.0884
-0.500 0.3265 0.02457 0.01241 -0.0656 0.7198 0.0895
-0.250 0.3530 0.02405 0.01174 -0.0647 0.7033 0.0911
0.000 0.3789 0.02361 0.01115 -0.0637 0.6866 0.0931
0.250 0.4045 0.02325 0.01063 -0.0627 0.6697 0.0961
0.500 0.4301 0.02297 0.01024 -0.0620 0.6515 0.1021
0.750 0.4558 0.02269 0.00989 -0.0613 0.6336 0.1101
1.000 0.4819 0.02248 0.00956 -0.0607 0.6162 0.1170
1.250 0.5082 0.02230 0.00928 -0.0600 0.5991 0.1283
1.500 0.5347 0.02190 0.00906 -0.0597 0.5828 0.1725
1.750 0.5611 0.02007 0.00889 -0.0587 0.5673 1.0000
2.000 0.5874 0.02037 0.00885 -0.0581 0.5525 1.0000
2.250 0.6138 0.02071 0.00892 -0.0577 0.5389 1.0000
2.500 0.6402 0.02108 0.00908 -0.0573 0.5270 1.0000
2.750 0.6667 0.02145 0.00923 -0.0569 0.5166 1.0000
3.000 0.6929 0.02191 0.00959 -0.0567 0.5052 1.0000
3.250 0.7192 0.02238 0.00995 -0.0565 0.4957 1.0000
3.500 0.7455 0.02283 0.01029 -0.0562 0.4873 1.0000
3.750 0.7716 0.02337 0.01081 -0.0561 0.4790 1.0000
4.000 0.7979 0.02388 0.01128 -0.0559 0.4724 1.0000
4.250 0.8240 0.02449 0.01189 -0.0558 0.4660 1.0000
4.500 0.8498 0.02509 0.01252 -0.0557 0.4597 1.0000
4.750 0.8762 0.02561 0.01300 -0.0555 0.4547 1.0000
5.000 0.9009 0.02639 0.01392 -0.0555 0.4481 1.0000
5.250 0.9265 0.02703 0.01462 -0.0553 0.4431 1.0000
5.500 0.9526 0.02767 0.01529 -0.0551 0.4392 1.0000
5.750 0.9762 0.02864 0.01647 -0.0551 0.4339 1.0000
6.000 1.0008 0.02943 0.01738 -0.0549 0.4291 1.0000
6.250 1.0267 0.03007 0.01810 -0.0547 0.4252 1.0000
6.500 1.0488 0.03121 0.01947 -0.0546 0.4200 1.0000
6.750 1.0717 0.03220 0.02066 -0.0544 0.4151 1.0000
7.000 1.0972 0.03283 0.02137 -0.0540 0.4106 1.0000
7.250 1.1168 0.03402 0.02285 -0.0536 0.4033 1.0000
7.500 1.1410 0.03460 0.02354 -0.0530 0.3968 1.0000
7.750 1.1608 0.03567 0.02484 -0.0525 0.3895 1.0000
8.000 1.1831 0.03646 0.02580 -0.0519 0.3827 1.0000
8.250 1.2043 0.03742 0.02700 -0.0513 0.3764 1.0000
8.500 1.2228 0.03853 0.02837 -0.0506 0.3687 1.0000
8.750 1.2437 0.03924 0.02926 -0.0497 0.3604 1.0000
9.000 1.2661 0.03956 0.02972 -0.0487 0.3503 1.0000
9.250 1.2799 0.04059 0.03107 -0.0474 0.3388 1.0000
9.500 1.2982 0.04106 0.03173 -0.0462 0.3273 1.0000
9.750 1.3206 0.04106 0.03184 -0.0450 0.3158 1.0000
10.000 1.3333 0.04175 0.03279 -0.0433 0.3026 1.0000
10.250 1.3397 0.04286 0.03421 -0.0414 0.2890 1.0000
10.500 1.3433 0.04423 0.03593 -0.0395 0.2762 1.0000
10.750 1.3436 0.04579 0.03779 -0.0375 0.2634 1.0000
11.000 1.3363 0.04775 0.04000 -0.0351 0.2507 1.0000
11.250 1.3228 0.05059 0.04306 -0.0335 0.2380 1.0000
11.500 1.3054 0.05464 0.04731 -0.0334 0.2250 1.0000
11.750 1.2864 0.05961 0.05244 -0.0344 0.2114 1.0000
12.000 1.2729 0.06409 0.05702 -0.0355 0.1947 1.0000
12.250 1.2756 0.06559 0.05824 -0.0351 0.1681 1.0000
12.500 1.2644 0.06969 0.06208 -0.0357 0.1500 1.0000
12.750 1.2489 0.07493 0.06722 -0.0370 0.1366 1.0000
13.000 1.2339 0.08034 0.07257 -0.0385 0.1248 1.0000
13.250 1.2208 0.08551 0.07767 -0.0398 0.1144 1.0000
13.500 1.2098 0.09028 0.08230 -0.0409 0.1053 1.0000
13.750 1.1994 0.09542 0.08753 -0.0423 0.0966 1.0000
14.000 1.1911 0.10016 0.09223 -0.0436 0.0889 1.0000
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Polar data table (+)
Polar graphs
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