GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 319 (HANSA-BRANDENBURG II) AIRFOIL (goe319-il) Reynolds number: 500,000 Max Cl/Cd: 91.06 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe319-il-500000-n5.txt Download as CSV file: xf-goe319-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2452 0.10094 0.09826 -0.0299 0.8553 0.0222
-9.000 -0.2406 0.09778 0.09504 -0.0318 0.8371 0.0222
-8.750 -0.2359 0.09459 0.09178 -0.0338 0.8183 0.0222
-8.500 -0.2311 0.09132 0.08844 -0.0362 0.8004 0.0223
-8.250 -0.2230 0.08830 0.08536 -0.0372 0.7851 0.0223
-8.000 -0.2121 0.08589 0.08289 -0.0371 0.7719 0.0225
-7.750 -0.2018 0.08354 0.08050 -0.0379 0.7604 0.0226
-7.500 -0.1919 0.08116 0.07807 -0.0393 0.7499 0.0229
-7.250 -0.1818 0.07867 0.07555 -0.0413 0.7403 0.0233
-7.000 -0.1685 0.07580 0.07263 -0.0445 0.7320 0.0238
-6.750 -0.1535 0.07257 0.06937 -0.0484 0.7242 0.0245
-6.500 -0.1330 0.06787 0.06457 -0.0566 0.7173 0.0255
-6.250 -0.1104 0.06319 0.05980 -0.0638 0.7113 0.0257
-6.000 -0.0877 0.05906 0.05558 -0.0687 0.7051 0.0257
-5.750 -0.0636 0.05489 0.05128 -0.0732 0.6991 0.0258
-5.500 -0.0451 0.05201 0.04835 -0.0748 0.6932 0.0260
-5.250 -0.0252 0.04999 0.04630 -0.0757 0.6864 0.0262
-5.000 -0.0031 0.04776 0.04399 -0.0772 0.6797 0.0264
-4.750 0.0208 0.04538 0.04154 -0.0790 0.6725 0.0267
-4.500 0.0457 0.04296 0.03902 -0.0807 0.6648 0.0271
-4.250 0.0717 0.04045 0.03638 -0.0825 0.6573 0.0277
-4.000 0.1069 0.03578 0.03138 -0.0856 0.6493 0.0296
-3.500 0.1574 0.02817 0.02328 -0.0874 0.6325 0.0256
-3.250 0.1829 0.02604 0.02095 -0.0877 0.6232 0.0255
-3.000 0.2092 0.02310 0.01772 -0.0877 0.6136 0.0254
-2.750 0.2352 0.01969 0.01388 -0.0875 0.6046 0.0255
-2.500 0.2611 0.01723 0.01096 -0.0870 0.5940 0.0256
-2.250 0.2874 0.01582 0.00921 -0.0867 0.5813 0.0260
-2.000 0.3139 0.01515 0.00836 -0.0864 0.5675 0.0263
-1.750 0.3407 0.01441 0.00741 -0.0860 0.5557 0.0264
-1.500 0.3680 0.01379 0.00663 -0.0858 0.5463 0.0266
-1.250 0.3952 0.01330 0.00600 -0.0855 0.5376 0.0268
-1.000 0.4226 0.01288 0.00546 -0.0852 0.5289 0.0271
-0.750 0.4499 0.01252 0.00500 -0.0849 0.5214 0.0274
-0.500 0.4775 0.01219 0.00458 -0.0847 0.5139 0.0278
-0.250 0.5048 0.01193 0.00423 -0.0844 0.5061 0.0281
0.000 0.5323 0.01168 0.00393 -0.0841 0.4987 0.0285
0.250 0.5596 0.01149 0.00368 -0.0838 0.4903 0.0289
0.500 0.5869 0.01135 0.00349 -0.0836 0.4823 0.0294
0.750 0.6141 0.01122 0.00332 -0.0833 0.4729 0.0300
1.000 0.6411 0.01106 0.00317 -0.0830 0.4632 0.0307
1.250 0.6679 0.01100 0.00307 -0.0827 0.4511 0.0312
1.500 0.6947 0.01097 0.00300 -0.0824 0.4365 0.0318
1.750 0.7214 0.01098 0.00295 -0.0821 0.4200 0.0325
2.000 0.7478 0.01104 0.00294 -0.0817 0.4010 0.0333
2.250 0.7738 0.01116 0.00296 -0.0814 0.3786 0.0340
2.500 0.7993 0.01133 0.00302 -0.0809 0.3548 0.0351
2.750 0.8248 0.01153 0.00312 -0.0805 0.3331 0.0370
3.000 0.8504 0.01174 0.00324 -0.0801 0.3143 0.0393
3.250 0.8761 0.01193 0.00337 -0.0797 0.2991 0.0426
3.500 0.9017 0.01212 0.00353 -0.0793 0.2858 0.0582
3.750 0.9272 0.01213 0.00377 -0.0790 0.2745 0.1881
4.250 0.9859 0.01109 0.00427 -0.0803 0.2568 1.0000
4.750 1.0360 0.01160 0.00465 -0.0793 0.2419 1.0000
5.250 1.0862 0.01210 0.00506 -0.0783 0.2320 1.0000
5.500 1.1115 0.01232 0.00525 -0.0779 0.2286 1.0000
5.750 1.1365 0.01256 0.00547 -0.0775 0.2252 1.0000
6.000 1.1610 0.01283 0.00572 -0.0769 0.2219 1.0000
6.250 1.1852 0.01312 0.00598 -0.0764 0.2185 1.0000
6.500 1.2102 0.01334 0.00621 -0.0760 0.2164 1.0000
6.750 1.2350 0.01357 0.00646 -0.0755 0.2137 1.0000
7.000 1.2593 0.01383 0.00672 -0.0750 0.2106 1.0000
7.250 1.2831 0.01412 0.00700 -0.0744 0.2075 1.0000
7.500 1.3063 0.01444 0.00731 -0.0738 0.2046 1.0000
7.750 1.3290 0.01479 0.00766 -0.0731 0.2017 1.0000
8.000 1.3530 0.01503 0.00794 -0.0726 0.1999 1.0000
8.250 1.3765 0.01530 0.00825 -0.0720 0.1976 1.0000
8.500 1.3994 0.01559 0.00857 -0.0714 0.1949 1.0000
8.750 1.4217 0.01592 0.00892 -0.0706 0.1921 1.0000
9.000 1.4430 0.01629 0.00929 -0.0698 0.1893 1.0000
9.250 1.4631 0.01672 0.00973 -0.0688 0.1861 1.0000
9.500 1.4854 0.01700 0.01006 -0.0681 0.1830 1.0000
9.750 1.5058 0.01734 0.01043 -0.0671 0.1785 1.0000
10.000 1.5236 0.01777 0.01087 -0.0658 0.1742 1.0000
10.250 1.5410 0.01823 0.01135 -0.0644 0.1707 1.0000
10.500 1.5597 0.01864 0.01181 -0.0633 0.1669 1.0000
10.750 1.5767 0.01914 0.01233 -0.0620 0.1622 1.0000
11.000 1.5918 0.01977 0.01296 -0.0606 0.1574 1.0000
11.250 1.6083 0.02035 0.01357 -0.0594 0.1519 1.0000
11.750 1.6358 0.02190 0.01514 -0.0567 0.1398 1.0000
12.000 1.6481 0.02281 0.01606 -0.0553 0.1345 1.0000
12.250 1.6603 0.02378 0.01705 -0.0541 0.1304 1.0000
12.500 1.6725 0.02477 0.01809 -0.0529 0.1263 1.0000
12.750 1.6826 0.02596 0.01931 -0.0517 0.1221 1.0000
13.000 1.6923 0.02722 0.02060 -0.0506 0.1185 1.0000
13.250 1.7027 0.02847 0.02191 -0.0496 0.1147 1.0000
13.500 1.7107 0.02996 0.02344 -0.0486 0.1108 1.0000
13.750 1.7168 0.03166 0.02517 -0.0476 0.1072 1.0000
14.000 1.7260 0.03312 0.02671 -0.0469 0.1041 1.0000
14.250 1.7327 0.03485 0.02850 -0.0461 0.1005 1.0000
14.500 1.7367 0.03686 0.03055 -0.0453 0.0973 1.0000
14.750 1.7419 0.03879 0.03255 -0.0447 0.0945 1.0000
15.000 1.7469 0.04077 0.03461 -0.0441 0.0907 1.0000
15.250 1.7469 0.04327 0.03714 -0.0435 0.0862 1.0000
15.500 1.7481 0.04569 0.03962 -0.0430 0.0817 1.0000
15.750 1.7460 0.04855 0.04253 -0.0426 0.0767 1.0000
16.000 1.7437 0.05152 0.04555 -0.0424 0.0724 1.0000
16.250 1.7386 0.05489 0.04896 -0.0423 0.0680 1.0000
16.500 1.7332 0.05840 0.05254 -0.0424 0.0645 1.0000
16.750 1.7266 0.06214 0.05635 -0.0426 0.0611 1.0000
17.000 1.7175 0.06629 0.06056 -0.0430 0.0582 1.0000
17.250 1.7088 0.07048 0.06483 -0.0435 0.0551 1.0000
17.500 1.6964 0.07527 0.06971 -0.0444 0.0522 1.0000
17.750 1.6845 0.08006 0.07459 -0.0453 0.0499 1.0000
18.000 1.6729 0.08491 0.07954 -0.0463 0.0476 1.0000
18.250 1.6574 0.09044 0.08517 -0.0477 0.0454 1.0000
18.500 1.6416 0.09610 0.09093 -0.0492 0.0435 1.0000
18.750 1.6260 0.10182 0.09676 -0.0509 0.0410 1.0000
19.000 1.6063 0.10835 0.10339 -0.0530 0.0386 1.0000
19.250 1.5876 0.11482 0.10996 -0.0553 0.0363 1.0000
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Polar data table (+)
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