GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.96 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe319-il-1000000.txt Download as CSV file: xf-goe319-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 319 (HANSA-BRANDENBURG II) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2409 0.09493 0.09300 -0.0302 0.8730 0.0205
-8.500 -0.2399 0.09129 0.08928 -0.0340 0.8528 0.0206
-8.250 -0.2357 0.08772 0.08564 -0.0371 0.8324 0.0206
-8.000 -0.2305 0.08391 0.08176 -0.0393 0.8126 0.0207
-7.750 -0.2202 0.08128 0.07907 -0.0393 0.7953 0.0208
-7.500 -0.2091 0.07876 0.07648 -0.0406 0.7800 0.0209
-7.000 -0.1814 0.07331 0.07093 -0.0457 0.7559 0.0212
-6.750 -0.1654 0.07044 0.06800 -0.0490 0.7462 0.0214
-6.500 -0.1478 0.06743 0.06495 -0.0526 0.7377 0.0217
-6.250 -0.1288 0.06434 0.06179 -0.0564 0.7299 0.0220
-6.000 -0.1080 0.06107 0.05848 -0.0604 0.7228 0.0225
-5.750 -0.0720 0.05451 0.05173 -0.0714 0.7161 0.0240
-5.500 -0.0462 0.05035 0.04745 -0.0754 0.7093 0.0240
-5.250 -0.0279 0.04645 0.04348 -0.0776 0.7019 0.0243
-5.000 -0.0063 0.04439 0.04133 -0.0787 0.6941 0.0244
-4.750 0.0170 0.04235 0.03925 -0.0799 0.6873 0.0246
-4.500 0.0412 0.04031 0.03713 -0.0811 0.6800 0.0248
-4.250 0.0665 0.03818 0.03490 -0.0824 0.6724 0.0252
-4.000 0.0927 0.03595 0.03256 -0.0836 0.6640 0.0256
-3.750 0.1198 0.03355 0.03003 -0.0848 0.6562 0.0264
-3.500 0.1526 0.02707 0.02313 -0.0866 0.6495 0.0281
-3.250 0.1772 0.02588 0.02184 -0.0867 0.6398 0.0284
-3.000 0.2026 0.02475 0.02062 -0.0869 0.6280 0.0287
-2.750 0.2286 0.02355 0.01931 -0.0870 0.6165 0.0291
-2.500 0.2552 0.02214 0.01773 -0.0869 0.6064 0.0299
-2.250 0.2834 0.01789 0.01292 -0.0863 0.5986 0.0325
-2.000 0.3096 0.01713 0.01208 -0.0862 0.5890 0.0328
-1.750 0.3364 0.01646 0.01132 -0.0861 0.5788 0.0333
-1.500 0.3633 0.01580 0.01055 -0.0859 0.5693 0.0339
-1.250 0.3924 0.01565 0.01007 -0.0853 0.5598 0.0368
-1.000 0.0313 0.02657 0.02306 -0.0755 0.5923 0.0286
-0.750 0.4459 0.01160 0.00539 -0.0842 0.5446 0.0324
-0.500 0.4736 0.01116 0.00489 -0.0839 0.5369 0.0317
-0.250 0.5012 0.01056 0.00421 -0.0837 0.5293 0.0314
0.000 0.5287 0.01020 0.00376 -0.0834 0.5216 0.0314
0.250 0.5565 0.00986 0.00338 -0.0832 0.5143 0.0314
0.500 0.5840 0.00975 0.00320 -0.0829 0.5062 0.0318
0.750 0.6119 0.00954 0.00296 -0.0827 0.4989 0.0322
1.000 0.6387 0.00921 0.00260 -0.0824 0.4902 0.0326
1.250 0.6662 0.00902 0.00241 -0.0821 0.4813 0.0332
1.500 0.6934 0.00897 0.00232 -0.0819 0.4706 0.0340
1.750 0.7211 0.00891 0.00225 -0.0817 0.4596 0.0348
2.000 0.7485 0.00891 0.00220 -0.0815 0.4474 0.0356
2.250 0.7757 0.00894 0.00218 -0.0813 0.4324 0.0364
2.500 0.8026 0.00899 0.00216 -0.0810 0.4133 0.0376
2.750 0.8288 0.00913 0.00220 -0.0807 0.3884 0.0400
3.000 0.8547 0.00936 0.00229 -0.0803 0.3590 0.0423
3.250 0.8800 0.00962 0.00242 -0.0798 0.3288 0.0486
3.500 0.9047 0.00968 0.00268 -0.0794 0.3035 0.2128
3.750 0.9404 0.00846 0.00304 -0.0818 0.2824 1.0000
4.000 0.9655 0.00872 0.00319 -0.0812 0.2690 1.0000
4.250 0.9906 0.00898 0.00336 -0.0807 0.2577 1.0000
4.500 1.0166 0.00916 0.00349 -0.0803 0.2514 1.0000
4.750 1.0421 0.00938 0.00366 -0.0799 0.2452 1.0000
5.000 1.0680 0.00958 0.00382 -0.0795 0.2404 1.0000
5.250 1.0941 0.00975 0.00397 -0.0792 0.2368 1.0000
5.500 1.1198 0.00995 0.00414 -0.0788 0.2329 1.0000
5.750 1.1451 0.01019 0.00434 -0.0784 0.2286 1.0000
6.000 1.1706 0.01040 0.00454 -0.0780 0.2253 1.0000
6.250 1.1968 0.01056 0.00470 -0.0777 0.2230 1.0000
6.500 1.2225 0.01074 0.00488 -0.0774 0.2201 1.0000
6.750 1.2478 0.01096 0.00509 -0.0770 0.2170 1.0000
7.000 1.2726 0.01122 0.00533 -0.0766 0.2136 1.0000
7.250 1.2968 0.01151 0.00561 -0.0761 0.2101 1.0000
7.500 1.3226 0.01167 0.00579 -0.0758 0.2086 1.0000
7.750 1.3481 0.01185 0.00599 -0.0755 0.2066 1.0000
8.000 1.3732 0.01205 0.00621 -0.0751 0.2041 1.0000
8.250 1.3977 0.01230 0.00646 -0.0747 0.2013 1.0000
8.500 1.4211 0.01261 0.00675 -0.0741 0.1974 1.0000
8.750 1.4449 0.01288 0.00703 -0.0736 0.1941 1.0000
9.000 1.4702 0.01304 0.00722 -0.0733 0.1914 1.0000
9.250 1.4944 0.01327 0.00746 -0.0729 0.1879 1.0000
9.500 1.5174 0.01357 0.00775 -0.0723 0.1839 1.0000
9.750 1.5395 0.01391 0.00809 -0.0716 0.1797 1.0000
10.000 1.5639 0.01410 0.00831 -0.0712 0.1758 1.0000
10.250 1.5861 0.01441 0.00860 -0.0706 0.1704 1.0000
10.500 1.6072 0.01478 0.00897 -0.0697 0.1654 1.0000
10.750 1.6293 0.01506 0.00928 -0.0690 0.1611 1.0000
11.000 1.6489 0.01548 0.00968 -0.0680 0.1551 1.0000
11.250 1.6671 0.01588 0.01008 -0.0667 0.1497 1.0000
11.500 1.6838 0.01635 0.01054 -0.0653 0.1440 1.0000
11.750 1.6992 0.01689 0.01109 -0.0637 0.1387 1.0000
12.000 1.7150 0.01743 0.01164 -0.0622 0.1340 1.0000
12.250 1.7278 0.01816 0.01235 -0.0605 0.1283 1.0000
12.500 1.7429 0.01878 0.01301 -0.0592 0.1246 1.0000
12.750 1.7564 0.01953 0.01377 -0.0577 0.1207 1.0000
13.000 1.7672 0.02048 0.01473 -0.0561 0.1160 1.0000
13.250 1.7813 0.02125 0.01555 -0.0550 0.1130 1.0000
13.500 1.7933 0.02220 0.01651 -0.0537 0.1094 1.0000
13.750 1.8024 0.02338 0.01772 -0.0523 0.1053 1.0000
14.000 1.8142 0.02442 0.01880 -0.0512 0.1023 1.0000
14.250 1.8250 0.02556 0.01998 -0.0502 0.0987 1.0000
14.500 1.8318 0.02706 0.02150 -0.0490 0.0944 1.0000
14.750 1.8408 0.02845 0.02293 -0.0480 0.0903 1.0000
15.000 1.8459 0.03019 0.02467 -0.0470 0.0848 1.0000
15.250 1.8507 0.03202 0.02654 -0.0461 0.0797 1.0000
15.500 1.8507 0.03435 0.02885 -0.0451 0.0732 1.0000
15.750 1.8499 0.03678 0.03129 -0.0442 0.0671 1.0000
16.000 1.8471 0.03949 0.03402 -0.0434 0.0619 1.0000
16.250 1.8409 0.04258 0.03714 -0.0427 0.0572 1.0000
16.500 1.8374 0.04550 0.04011 -0.0421 0.0534 1.0000
16.750 1.8288 0.04909 0.04374 -0.0418 0.0494 1.0000
17.000 1.8228 0.05249 0.04720 -0.0416 0.0455 1.0000
17.250 1.8111 0.05669 0.05144 -0.0416 0.0414 1.0000
17.500 1.7963 0.06141 0.05620 -0.0419 0.0365 1.0000
17.750 1.7788 0.06660 0.06144 -0.0425 0.0313 1.0000
18.000 1.7577 0.07245 0.06735 -0.0434 0.0264 1.0000
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Polar data table (+)
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