GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Reynolds number: 100,000 Max Cl/Cd: 54.07 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe314-il-100000-n5.txt Download as CSV file: xf-goe314-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 314 (HANSA-BRANDENBURG) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3034 0.09562 0.09068 -0.0240 1.0000 0.0503
-7.750 -0.3055 0.09355 0.08868 -0.0243 1.0000 0.0514
-7.500 -0.3125 0.09197 0.08720 -0.0246 1.0000 0.0522
-7.250 -0.3167 0.09025 0.08556 -0.0271 1.0000 0.0527
-7.000 -0.3175 0.08833 0.08369 -0.0302 1.0000 0.0530
-6.750 -0.3159 0.08623 0.08160 -0.0327 1.0000 0.0532
-6.500 -0.3147 0.08263 0.07809 -0.0307 1.0000 0.0536
-6.250 -0.3139 0.07941 0.07497 -0.0262 1.0000 0.0545
-6.000 -0.3030 0.07642 0.07199 -0.0263 0.9971 0.0559
-5.750 -0.2735 0.07241 0.06793 -0.0320 0.9880 0.0580
-5.500 -0.2416 0.06841 0.06383 -0.0389 0.9776 0.0605
-5.250 -0.1891 0.06531 0.06024 -0.0530 0.9637 0.0636
-5.000 -0.1700 0.06029 0.05532 -0.0542 0.9546 0.0645
-4.750 -0.1464 0.05671 0.05178 -0.0555 0.9470 0.0667
-4.500 -0.1179 0.05376 0.04875 -0.0585 0.9354 0.0704
-4.000 -0.0443 0.04729 0.04176 -0.0680 0.9142 0.0770
-3.750 -0.0175 0.04439 0.03882 -0.0695 0.9024 0.0791
-3.500 0.0130 0.04194 0.03623 -0.0716 0.8897 0.0827
-3.250 0.0507 0.03986 0.03371 -0.0746 0.8768 0.0896
-3.000 0.0771 0.03725 0.03112 -0.0756 0.8637 0.0937
-2.750 0.1116 0.03568 0.02913 -0.0773 0.8496 0.1030
-2.500 0.1386 0.03333 0.02672 -0.0780 0.8345 0.1053
-2.250 0.1770 0.02976 0.02241 -0.0781 0.8203 0.0619
-2.000 0.2045 0.02794 0.02036 -0.0781 0.8039 0.0599
-1.750 0.2322 0.02632 0.01843 -0.0777 0.7864 0.0581
-1.500 0.2591 0.02508 0.01691 -0.0772 0.7677 0.0590
-1.250 0.2861 0.02397 0.01552 -0.0766 0.7483 0.0603
-1.000 0.3131 0.02284 0.01409 -0.0760 0.7279 0.0598
-0.750 0.3401 0.02181 0.01275 -0.0753 0.7071 0.0592
-0.500 0.3664 0.02093 0.01160 -0.0745 0.6844 0.0591
-0.250 0.3929 0.02015 0.01055 -0.0737 0.6618 0.0592
0.000 0.4192 0.01949 0.00963 -0.0729 0.6389 0.0597
0.250 0.4454 0.01899 0.00888 -0.0721 0.6167 0.0615
0.500 0.4714 0.01863 0.00826 -0.0713 0.5962 0.0640
0.750 0.4968 0.01812 0.00766 -0.0706 0.5768 0.0656
1.000 0.5222 0.01777 0.00721 -0.0698 0.5593 0.0670
1.250 0.5475 0.01750 0.00684 -0.0691 0.5433 0.0687
1.500 0.5724 0.01729 0.00654 -0.0683 0.5288 0.0709
1.750 0.5976 0.01720 0.00631 -0.0675 0.5153 0.0750
2.000 0.6231 0.01710 0.00619 -0.0669 0.5020 0.0807
2.250 0.6486 0.01710 0.00607 -0.0663 0.4890 0.0857
2.500 0.6739 0.01712 0.00598 -0.0656 0.4760 0.0918
2.750 0.6990 0.01718 0.00596 -0.0650 0.4638 0.1056
3.000 0.7241 0.01720 0.00596 -0.0643 0.4521 0.1299
3.500 0.7934 0.01598 0.00625 -0.0672 0.4284 1.0000
3.750 0.8173 0.01629 0.00641 -0.0663 0.4192 1.0000
4.000 0.8414 0.01657 0.00664 -0.0656 0.4092 1.0000
4.250 0.8653 0.01688 0.00686 -0.0647 0.4007 1.0000
4.500 0.8892 0.01718 0.00715 -0.0640 0.3916 1.0000
4.750 0.9130 0.01751 0.00743 -0.0632 0.3832 1.0000
5.000 0.9367 0.01783 0.00774 -0.0624 0.3742 1.0000
5.250 0.9600 0.01815 0.00807 -0.0616 0.3647 1.0000
5.500 0.9828 0.01849 0.00834 -0.0606 0.3548 1.0000
5.750 1.0055 0.01880 0.00869 -0.0597 0.3433 1.0000
6.000 1.0279 0.01913 0.00905 -0.0588 0.3322 1.0000
6.250 1.0499 0.01948 0.00937 -0.0578 0.3222 1.0000
6.500 1.0723 0.01985 0.00979 -0.0569 0.3120 1.0000
6.750 1.0944 0.02024 0.01021 -0.0559 0.3029 1.0000
7.000 1.1161 0.02064 0.01065 -0.0549 0.2943 1.0000
7.250 1.1383 0.02107 0.01116 -0.0540 0.2864 1.0000
7.500 1.1597 0.02152 0.01164 -0.0530 0.2792 1.0000
7.750 1.1811 0.02198 0.01220 -0.0521 0.2712 1.0000
8.000 1.2017 0.02245 0.01273 -0.0510 0.2638 1.0000
8.250 1.2226 0.02295 0.01334 -0.0500 0.2566 1.0000
8.500 1.2427 0.02345 0.01391 -0.0489 0.2497 1.0000
8.750 1.2626 0.02397 0.01455 -0.0477 0.2427 1.0000
9.000 1.2817 0.02451 0.01521 -0.0465 0.2358 1.0000
9.250 1.3006 0.02507 0.01589 -0.0453 0.2297 1.0000
9.500 1.3195 0.02566 0.01665 -0.0441 0.2238 1.0000
9.750 1.3361 0.02626 0.01732 -0.0426 0.2168 1.0000
10.000 1.3521 0.02688 0.01814 -0.0410 0.2075 1.0000
10.250 1.3659 0.02755 0.01893 -0.0392 0.1969 1.0000
10.500 1.3769 0.02832 0.01978 -0.0371 0.1839 1.0000
10.750 1.3842 0.02921 0.02073 -0.0346 0.1675 1.0000
11.000 1.3887 0.03028 0.02184 -0.0318 0.1492 1.0000
11.250 1.3910 0.03160 0.02316 -0.0291 0.1198 1.0000
11.500 1.3790 0.03394 0.02520 -0.0257 0.0872 1.0000
11.750 1.3686 0.03654 0.02773 -0.0231 0.0773 1.0000
12.000 1.3588 0.03937 0.03059 -0.0213 0.0717 1.0000
12.250 1.3501 0.04238 0.03372 -0.0201 0.0680 1.0000
12.500 1.3376 0.04607 0.03753 -0.0195 0.0648 1.0000
12.750 1.3229 0.05041 0.04200 -0.0197 0.0626 1.0000
13.000 1.3091 0.05504 0.04678 -0.0206 0.0605 1.0000
13.250 1.2961 0.05996 0.05189 -0.0219 0.0583 1.0000
13.500 1.2812 0.06543 0.05755 -0.0237 0.0566 1.0000
13.750 1.2646 0.07138 0.06366 -0.0259 0.0551 1.0000
14.000 1.2480 0.07745 0.06986 -0.0281 0.0536 1.0000
14.250 1.2319 0.08353 0.07605 -0.0304 0.0523 1.0000
14.500 1.2161 0.08956 0.08211 -0.0326 0.0505 1.0000
14.750 1.2084 0.09458 0.08733 -0.0345 0.0482 1.0000
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Polar data table (+)
Polar graphs
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