GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Reynolds number: 1,000,000 Max Cl/Cd: 112.83 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe319-il-1000000-n5.txt Download as CSV file: xf-goe319-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2463 0.09317 0.09054 -0.0292 0.7276 0.0155
-8.500 -0.2397 0.08995 0.08729 -0.0310 0.7199 0.0157
-8.250 -0.2434 0.08377 0.08108 -0.0356 0.7140 0.0164
-8.000 -0.2329 0.08151 0.07882 -0.0370 0.7076 0.0165
-7.750 -0.2223 0.07925 0.07654 -0.0388 0.7013 0.0166
-7.500 -0.2102 0.07689 0.07416 -0.0412 0.6960 0.0167
-7.250 -0.1953 0.07429 0.07156 -0.0443 0.6908 0.0169
-7.000 -0.1793 0.07140 0.06865 -0.0479 0.6852 0.0172
-6.750 -0.1625 0.06798 0.06518 -0.0522 0.6797 0.0174
-6.500 -0.1438 0.06443 0.06160 -0.0567 0.6746 0.0176
-6.250 -0.1235 0.06080 0.05792 -0.0612 0.6681 0.0177
-6.000 -0.1018 0.05711 0.05415 -0.0656 0.6611 0.0179
-5.750 -0.0784 0.05329 0.05026 -0.0699 0.6545 0.0181
-5.500 -0.0538 0.04926 0.04613 -0.0741 0.6468 0.0184
-5.250 -0.0251 0.04149 0.03811 -0.0810 0.6412 0.0193
-5.000 -0.0003 0.03925 0.03577 -0.0825 0.6323 0.0194
-4.750 0.0249 0.03715 0.03357 -0.0838 0.6224 0.0195
-4.500 0.0505 0.03496 0.03125 -0.0849 0.6109 0.0197
-4.250 0.0766 0.03250 0.02864 -0.0860 0.6012 0.0198
-4.000 0.1029 0.02989 0.02586 -0.0869 0.5915 0.0199
-3.750 0.1293 0.02750 0.02329 -0.0875 0.5809 0.0201
-3.500 0.1557 0.02499 0.02057 -0.0879 0.5702 0.0205
-3.250 0.1772 0.01481 0.00930 -0.0873 0.5641 0.0216
-3.000 0.2029 0.01314 0.00724 -0.0869 0.5520 0.0218
-2.750 0.2296 0.01245 0.00630 -0.0866 0.5368 0.0220
-2.250 0.2841 0.01143 0.00496 -0.0860 0.5146 0.0224
-2.000 0.3116 0.01102 0.00447 -0.0858 0.5072 0.0226
-1.750 0.3394 0.01075 0.00414 -0.0856 0.5012 0.0228
-1.500 0.3672 0.01053 0.00387 -0.0855 0.4944 0.0230
-1.250 0.3949 0.01035 0.00363 -0.0853 0.4873 0.0232
-1.000 0.4229 0.01016 0.00341 -0.0851 0.4809 0.0235
-0.750 0.4507 0.01000 0.00320 -0.0849 0.4730 0.0238
-0.500 0.4784 0.00985 0.00301 -0.0847 0.4657 0.0241
-0.250 0.5061 0.00972 0.00284 -0.0845 0.4566 0.0244
0.000 0.5337 0.00962 0.00269 -0.0843 0.4471 0.0247
0.250 0.5611 0.00956 0.00257 -0.0841 0.4343 0.0250
0.500 0.5883 0.00954 0.00247 -0.0838 0.4182 0.0252
0.750 0.6154 0.00956 0.00241 -0.0836 0.3992 0.0255
1.000 0.6422 0.00963 0.00239 -0.0833 0.3775 0.0257
1.250 0.6684 0.00969 0.00234 -0.0829 0.3539 0.0264
1.500 0.6948 0.00981 0.00237 -0.0826 0.3317 0.0270
1.750 0.7212 0.00994 0.00242 -0.0823 0.3116 0.0276
2.000 0.7478 0.01007 0.00247 -0.0820 0.2948 0.0281
2.250 0.7745 0.01019 0.00253 -0.0817 0.2813 0.0287
2.500 0.8012 0.01032 0.00260 -0.0815 0.2693 0.0293
2.750 0.8283 0.01041 0.00266 -0.0813 0.2604 0.0299
3.000 0.8550 0.01053 0.00274 -0.0810 0.2512 0.0311
3.250 0.8820 0.01064 0.00283 -0.0808 0.2433 0.0324
3.500 0.9085 0.01079 0.00294 -0.0806 0.2350 0.0343
3.750 0.9356 0.01088 0.00303 -0.0804 0.2301 0.0383
4.000 0.9624 0.01094 0.00318 -0.0802 0.2254 0.0871
4.250 0.9887 0.01096 0.00337 -0.0800 0.2202 0.2030
4.750 1.0481 0.00978 0.00382 -0.0814 0.2144 1.0000
5.000 1.0743 0.00994 0.00395 -0.0811 0.2120 1.0000
5.250 1.1004 0.01011 0.00410 -0.0807 0.2094 1.0000
5.500 1.1262 0.01030 0.00426 -0.0804 0.2064 1.0000
5.750 1.1518 0.01051 0.00444 -0.0800 0.2029 1.0000
6.000 1.1778 0.01068 0.00460 -0.0797 0.2008 1.0000
6.250 1.2039 0.01083 0.00476 -0.0794 0.1992 1.0000
6.500 1.2298 0.01100 0.00493 -0.0791 0.1972 1.0000
6.750 1.2555 0.01119 0.00512 -0.0788 0.1950 1.0000
7.000 1.2809 0.01139 0.00531 -0.0785 0.1926 1.0000
7.250 1.3059 0.01162 0.00552 -0.0781 0.1899 1.0000
7.500 1.3307 0.01186 0.00576 -0.0777 0.1870 1.0000
7.750 1.3559 0.01206 0.00597 -0.0773 0.1853 1.0000
8.000 1.3811 0.01225 0.00618 -0.0770 0.1835 1.0000
8.250 1.4059 0.01246 0.00640 -0.0766 0.1809 1.0000
8.500 1.4300 0.01272 0.00665 -0.0761 0.1766 1.0000
8.750 1.4533 0.01303 0.00693 -0.0756 0.1716 1.0000
9.000 1.4775 0.01326 0.00718 -0.0751 0.1685 1.0000
9.250 1.5010 0.01353 0.00745 -0.0746 0.1642 1.0000
9.500 1.5233 0.01387 0.00777 -0.0739 0.1591 1.0000
9.750 1.5458 0.01418 0.00808 -0.0733 0.1540 1.0000
10.000 1.5664 0.01461 0.00846 -0.0724 0.1461 1.0000
10.250 1.5865 0.01504 0.00886 -0.0714 0.1383 1.0000
10.500 1.6049 0.01555 0.00934 -0.0702 0.1307 1.0000
10.750 1.6229 0.01600 0.00978 -0.0689 0.1255 1.0000
11.000 1.6383 0.01654 0.01031 -0.0672 0.1204 1.0000
11.250 1.6553 0.01701 0.01079 -0.0658 0.1171 1.0000
11.500 1.6713 0.01753 0.01134 -0.0644 0.1137 1.0000
11.750 1.6854 0.01819 0.01200 -0.0628 0.1098 1.0000
12.000 1.7002 0.01883 0.01267 -0.0614 0.1063 1.0000
12.250 1.7144 0.01954 0.01339 -0.0600 0.1023 1.0000
12.500 1.7267 0.02039 0.01425 -0.0585 0.0983 1.0000
12.750 1.7398 0.02123 0.01511 -0.0572 0.0952 1.0000
13.000 1.7533 0.02207 0.01599 -0.0560 0.0918 1.0000
13.250 1.7629 0.02321 0.01713 -0.0546 0.0867 1.0000
13.500 1.7730 0.02437 0.01831 -0.0534 0.0817 1.0000
13.750 1.7793 0.02587 0.01979 -0.0520 0.0752 1.0000
14.000 1.7846 0.02751 0.02143 -0.0507 0.0687 1.0000
14.250 1.7894 0.02927 0.02320 -0.0495 0.0635 1.0000
14.500 1.7916 0.03131 0.02524 -0.0484 0.0586 1.0000
14.750 1.7952 0.03331 0.02728 -0.0474 0.0545 1.0000
15.000 1.7958 0.03562 0.02962 -0.0465 0.0509 1.0000
15.250 1.7988 0.03775 0.03179 -0.0458 0.0480 1.0000
15.500 1.7973 0.04037 0.03446 -0.0451 0.0448 1.0000
15.750 1.7964 0.04296 0.03710 -0.0445 0.0415 1.0000
16.000 1.7914 0.04608 0.04026 -0.0439 0.0378 1.0000
16.250 1.7845 0.04953 0.04374 -0.0436 0.0331 1.0000
16.500 1.7661 0.05443 0.04866 -0.0435 0.0249 1.0000
16.750 1.7483 0.05950 0.05378 -0.0437 0.0198 1.0000
17.000 1.7353 0.06415 0.05850 -0.0441 0.0175 1.0000
17.250 1.7256 0.06848 0.06292 -0.0447 0.0164 1.0000
17.500 1.7149 0.07304 0.06757 -0.0454 0.0155 1.0000
18.000 1.6919 0.08259 0.07733 -0.0472 0.0143 1.0000
18.250 1.6797 0.08761 0.08245 -0.0483 0.0139 1.0000
18.500 1.6658 0.09297 0.08793 -0.0497 0.0136 1.0000
18.750 1.6500 0.09869 0.09376 -0.0513 0.0133 1.0000
19.000 1.6330 0.10470 0.09989 -0.0531 0.0130 1.0000
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Polar data table (+)
Polar graphs
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