GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL (goe322-il) Reynolds number: 500,000 Max Cl/Cd: 95.72 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe322-il-500000-n5.txt Download as CSV file: xf-goe322-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2349 0.10124 0.09781 -0.0308 0.6881 0.0181
-9.250 -0.2315 0.09726 0.09382 -0.0330 0.6851 0.0185
-9.000 -0.2389 0.09064 0.08720 -0.0376 0.6827 0.0192
-8.750 -0.2282 0.08860 0.08515 -0.0383 0.6796 0.0194
-8.500 -0.2183 0.08635 0.08290 -0.0395 0.6766 0.0196
-8.250 -0.2091 0.08389 0.08045 -0.0410 0.6731 0.0199
-8.000 -0.2011 0.08114 0.07770 -0.0430 0.6695 0.0203
-7.750 -0.1958 0.07801 0.07457 -0.0454 0.6659 0.0208
-7.500 -0.1892 0.07418 0.07071 -0.0496 0.6627 0.0211
-7.250 -0.1788 0.06960 0.06612 -0.0552 0.6594 0.0213
-7.000 -0.1658 0.06462 0.06110 -0.0612 0.6559 0.0216
-6.750 -0.1532 0.05216 0.04841 -0.0747 0.6534 0.0229
-6.500 -0.1354 0.04769 0.04380 -0.0781 0.6499 0.0231
-6.250 -0.1145 0.04479 0.04077 -0.0801 0.6465 0.0233
-6.000 -0.0922 0.04182 0.03769 -0.0820 0.6429 0.0235
-5.750 -0.0693 0.03832 0.03403 -0.0839 0.6387 0.0237
-5.500 -0.0457 0.03476 0.03026 -0.0854 0.6345 0.0241
-5.250 -0.0213 0.03156 0.02682 -0.0865 0.6306 0.0247
-5.000 -0.0017 0.02152 0.01579 -0.0879 0.6278 0.0254
-4.750 0.0245 0.01917 0.01302 -0.0881 0.6236 0.0257
-4.500 0.0518 0.01776 0.01131 -0.0882 0.6189 0.0260
-4.250 0.0796 0.01682 0.01011 -0.0882 0.6139 0.0264
-4.000 0.1080 0.01608 0.00918 -0.0883 0.6076 0.0268
-3.750 0.1363 0.01541 0.00832 -0.0884 0.6003 0.0270
-3.500 0.1648 0.01485 0.00760 -0.0885 0.5929 0.0271
-3.250 0.1934 0.01441 0.00701 -0.0886 0.5850 0.0273
-3.000 0.2217 0.01375 0.00623 -0.0887 0.5784 0.0276
-2.750 0.2501 0.01321 0.00562 -0.0888 0.5720 0.0279
-2.250 0.3072 0.01251 0.00482 -0.0890 0.5607 0.0286
-2.000 0.3359 0.01224 0.00451 -0.0891 0.5550 0.0289
-1.750 0.3644 0.01202 0.00424 -0.0892 0.5496 0.0293
-1.500 0.3932 0.01180 0.00399 -0.0894 0.5437 0.0297
-1.250 0.4219 0.01162 0.00378 -0.0895 0.5378 0.0302
-1.000 0.4505 0.01149 0.00361 -0.0896 0.5327 0.0309
-0.750 0.4794 0.01134 0.00345 -0.0898 0.5275 0.0316
-0.500 0.5081 0.01123 0.00331 -0.0899 0.5217 0.0320
-0.250 0.5368 0.01115 0.00319 -0.0901 0.5161 0.0324
0.000 0.5656 0.01104 0.00306 -0.0903 0.5086 0.0330
0.500 0.6228 0.01093 0.00290 -0.0906 0.4945 0.0351
0.750 0.6514 0.01092 0.00286 -0.0907 0.4877 0.0363
1.000 0.6800 0.01092 0.00283 -0.0909 0.4811 0.0379
1.250 0.7084 0.01092 0.00283 -0.0911 0.4719 0.0420
1.500 0.7367 0.01090 0.00288 -0.0912 0.4617 0.0680
1.750 0.7647 0.01095 0.00291 -0.0914 0.4514 0.0859
2.000 0.7930 0.01095 0.00299 -0.0915 0.4420 0.1172
2.250 0.8210 0.01100 0.00307 -0.0917 0.4329 0.1515
2.500 0.8486 0.01105 0.00316 -0.0918 0.4207 0.1897
3.000 0.9010 0.00969 0.00350 -0.0918 0.3921 1.0000
3.250 0.9279 0.00992 0.00363 -0.0918 0.3791 1.0000
3.500 0.9547 0.01016 0.00378 -0.0917 0.3675 1.0000
3.750 0.9813 0.01041 0.00395 -0.0917 0.3568 1.0000
4.000 1.0079 0.01066 0.00412 -0.0916 0.3465 1.0000
4.250 1.0343 0.01091 0.00431 -0.0916 0.3374 1.0000
4.500 1.0604 0.01119 0.00452 -0.0915 0.3285 1.0000
4.750 1.0868 0.01142 0.00471 -0.0914 0.3213 1.0000
5.000 1.1129 0.01168 0.00493 -0.0913 0.3144 1.0000
5.250 1.1388 0.01194 0.00515 -0.0912 0.3084 1.0000
5.500 1.1649 0.01217 0.00537 -0.0911 0.3024 1.0000
5.750 1.1902 0.01246 0.00562 -0.0909 0.2962 1.0000
6.000 1.2158 0.01271 0.00586 -0.0908 0.2909 1.0000
6.250 1.2412 0.01298 0.00611 -0.0906 0.2848 1.0000
6.500 1.2654 0.01331 0.00642 -0.0903 0.2788 1.0000
6.750 1.2903 0.01358 0.00669 -0.0901 0.2710 1.0000
7.000 1.3132 0.01398 0.00703 -0.0896 0.2603 1.0000
7.250 1.3354 0.01442 0.00740 -0.0890 0.2488 1.0000
7.500 1.3578 0.01482 0.00777 -0.0884 0.2377 1.0000
7.750 1.3786 0.01529 0.00820 -0.0877 0.2256 1.0000
8.000 1.3982 0.01582 0.00867 -0.0868 0.2134 1.0000
8.250 1.4155 0.01647 0.00923 -0.0855 0.1992 1.0000
8.500 1.4314 0.01713 0.00983 -0.0841 0.1877 1.0000
8.750 1.4455 0.01781 0.01047 -0.0823 0.1786 1.0000
9.000 1.4585 0.01844 0.01110 -0.0804 0.1725 1.0000
9.250 1.4700 0.01922 0.01188 -0.0784 0.1658 1.0000
9.500 1.4818 0.02007 0.01273 -0.0767 0.1596 1.0000
9.750 1.4930 0.02104 0.01370 -0.0752 0.1527 1.0000
10.000 1.5035 0.02217 0.01482 -0.0739 0.1460 1.0000
10.250 1.5123 0.02352 0.01615 -0.0726 0.1361 1.0000
10.500 1.5166 0.02536 0.01792 -0.0713 0.1190 1.0000
10.750 1.4912 0.02994 0.02218 -0.0687 0.0679 1.0000
11.000 1.4679 0.03452 0.02663 -0.0664 0.0270 1.0000
11.250 1.4651 0.03729 0.02940 -0.0653 0.0172 1.0000
11.500 1.4692 0.03941 0.03159 -0.0645 0.0156 1.0000
11.750 1.4734 0.04156 0.03382 -0.0638 0.0145 1.0000
12.000 1.4782 0.04367 0.03600 -0.0632 0.0138 1.0000
12.250 1.4817 0.04592 0.03833 -0.0626 0.0132 1.0000
12.500 1.4839 0.04834 0.04085 -0.0620 0.0127 1.0000
12.750 1.4851 0.05095 0.04355 -0.0616 0.0123 1.0000
13.000 1.4847 0.05383 0.04652 -0.0612 0.0119 1.0000
13.250 1.4851 0.05671 0.04949 -0.0609 0.0115 1.0000
13.500 1.4864 0.05955 0.05242 -0.0608 0.0112 1.0000
13.750 1.4866 0.06258 0.05555 -0.0607 0.0109 1.0000
14.000 1.4858 0.06577 0.05883 -0.0607 0.0106 1.0000
14.250 1.4842 0.06913 0.06230 -0.0608 0.0103 1.0000
14.500 1.4812 0.07273 0.06599 -0.0610 0.0100 1.0000
14.750 1.4771 0.07653 0.06989 -0.0614 0.0098 1.0000
15.000 1.4712 0.08061 0.07407 -0.0618 0.0096 1.0000
15.250 1.4637 0.08501 0.07857 -0.0623 0.0094 1.0000
15.500 1.4542 0.08977 0.08344 -0.0630 0.0093 1.0000
15.750 1.4426 0.09491 0.08870 -0.0639 0.0091 1.0000
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Polar data table (+)
Polar graphs
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