GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Reynolds number: 200,000 Max Cl/Cd: 77.18 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe326-il-200000.txt Download as CSV file: xf-goe326-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 326 (PFALZ 55) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3258 0.08940 0.08615 -0.0263 1.0000 0.0383
-7.250 -0.3237 0.08752 0.08434 -0.0334 1.0000 0.0391
-7.000 -0.3251 0.08558 0.08245 -0.0359 1.0000 0.0393
-6.750 -0.3334 0.08408 0.08099 -0.0350 1.0000 0.0394
-6.250 -0.3094 0.07389 0.07083 -0.0379 0.9944 0.0405
-6.000 -0.2845 0.06990 0.06683 -0.0405 0.9891 0.0418
-5.750 -0.2505 0.06551 0.06237 -0.0471 0.9841 0.0439
-5.500 -0.1835 0.06061 0.05704 -0.0651 0.9751 0.0500
-5.250 -0.1541 0.05351 0.04987 -0.0709 0.9713 0.0512
-5.000 -0.1300 0.05011 0.04651 -0.0726 0.9649 0.0526
-4.750 -0.0961 0.04679 0.04311 -0.0766 0.9596 0.0555
-4.500 -0.0433 0.04260 0.03824 -0.0850 0.9524 0.0635
-4.250 -0.0185 0.03872 0.03450 -0.0869 0.9457 0.0655
-4.000 0.0111 0.03632 0.03203 -0.0887 0.9381 0.0689
-3.750 0.0501 0.03347 0.02859 -0.0918 0.9298 0.0782
-3.500 0.0729 0.03114 0.02637 -0.0922 0.9201 0.0815
-3.250 0.1048 0.02936 0.02414 -0.0932 0.9117 0.0932
-3.000 0.1274 0.02744 0.02227 -0.0930 0.9008 0.0970
-2.750 0.1540 0.02598 0.02050 -0.0929 0.8901 0.1095
-2.500 0.1797 0.02485 0.01916 -0.0926 0.8799 0.1238
-2.250 0.2035 0.02357 0.01781 -0.0921 0.8692 0.1397
-1.500 0.2926 0.01816 0.01115 -0.0895 0.8372 0.0879
-1.250 0.3216 0.01743 0.00996 -0.0883 0.8252 0.0772
-1.000 0.3484 0.01661 0.00899 -0.0876 0.8127 0.0770
-0.750 0.3751 0.01535 0.00760 -0.0869 0.8004 0.0754
-0.500 0.4019 0.01459 0.00671 -0.0862 0.7874 0.0749
-0.250 0.4287 0.01402 0.00603 -0.0854 0.7740 0.0753
0.000 0.4553 0.01358 0.00551 -0.0847 0.7596 0.0763
0.250 0.4815 0.01299 0.00489 -0.0841 0.7448 0.0794
0.500 0.5077 0.01266 0.00456 -0.0835 0.7291 0.0843
0.750 0.5343 0.01242 0.00428 -0.0829 0.7129 0.0884
1.000 0.5609 0.01220 0.00400 -0.0824 0.6963 0.0949
1.250 0.5878 0.01203 0.00381 -0.0820 0.6794 0.1111
1.500 0.6155 0.00994 0.00371 -0.0818 0.6630 1.0000
1.750 0.6422 0.01006 0.00363 -0.0812 0.6460 1.0000
2.000 0.6688 0.01019 0.00359 -0.0808 0.6293 1.0000
2.250 0.6954 0.01032 0.00361 -0.0804 0.6117 1.0000
2.500 0.7218 0.01048 0.00364 -0.0800 0.5942 1.0000
2.750 0.7480 0.01067 0.00369 -0.0795 0.5772 1.0000
3.000 0.7742 0.01091 0.00380 -0.0791 0.5613 1.0000
3.250 0.8003 0.01117 0.00394 -0.0787 0.5461 1.0000
3.500 0.8264 0.01146 0.00412 -0.0784 0.5313 1.0000
3.750 0.8524 0.01175 0.00434 -0.0780 0.5166 1.0000
4.000 0.8785 0.01204 0.00456 -0.0776 0.5028 1.0000
4.250 0.9045 0.01234 0.00481 -0.0773 0.4902 1.0000
4.500 0.9306 0.01265 0.00506 -0.0770 0.4786 1.0000
4.750 0.9566 0.01294 0.00533 -0.0767 0.4668 1.0000
5.000 0.9824 0.01318 0.00559 -0.0763 0.4540 1.0000
5.250 1.0082 0.01344 0.00587 -0.0760 0.4419 1.0000
5.500 1.0339 0.01371 0.00616 -0.0756 0.4303 1.0000
5.750 1.0593 0.01398 0.00643 -0.0752 0.4186 1.0000
6.000 1.0844 0.01425 0.00669 -0.0748 0.4064 1.0000
6.250 1.1095 0.01450 0.00699 -0.0743 0.3939 1.0000
6.500 1.1340 0.01476 0.00729 -0.0738 0.3794 1.0000
6.750 1.1579 0.01504 0.00756 -0.0732 0.3631 1.0000
7.000 1.1816 0.01531 0.00788 -0.0726 0.3445 1.0000
7.250 1.2046 0.01563 0.00821 -0.0719 0.3236 1.0000
7.500 1.2271 0.01603 0.00861 -0.0711 0.3032 1.0000
7.750 1.2491 0.01647 0.00905 -0.0703 0.2777 1.0000
8.000 1.2697 0.01704 0.00955 -0.0694 0.2470 1.0000
8.250 1.2892 0.01776 0.01015 -0.0683 0.2093 1.0000
8.500 1.3059 0.01874 0.01094 -0.0670 0.1677 1.0000
8.750 1.3218 0.01982 0.01183 -0.0656 0.1404 1.0000
9.000 1.3371 0.02090 0.01282 -0.0642 0.1218 1.0000
9.250 1.3535 0.02186 0.01377 -0.0628 0.1044 1.0000
9.500 1.3693 0.02284 0.01470 -0.0613 0.0804 1.0000
9.750 1.3770 0.02446 0.01601 -0.0589 0.0434 1.0000
10.000 1.3833 0.02604 0.01753 -0.0562 0.0339 1.0000
10.250 1.3889 0.02739 0.01897 -0.0533 0.0305 1.0000
10.500 1.3942 0.02881 0.02051 -0.0507 0.0286 1.0000
10.750 1.3971 0.03048 0.02230 -0.0482 0.0273 1.0000
11.000 1.3970 0.03252 0.02447 -0.0459 0.0263 1.0000
11.250 1.3936 0.03497 0.02706 -0.0437 0.0255 1.0000
11.500 1.3917 0.03748 0.02970 -0.0421 0.0251 1.0000
11.750 1.3913 0.04001 0.03237 -0.0408 0.0247 1.0000
12.000 1.3903 0.04271 0.03523 -0.0397 0.0244 1.0000
12.250 1.3894 0.04551 0.03816 -0.0388 0.0240 1.0000
12.500 1.3885 0.04837 0.04115 -0.0381 0.0235 1.0000
12.750 1.3878 0.05127 0.04417 -0.0374 0.0229 1.0000
13.000 1.3869 0.05424 0.04724 -0.0368 0.0223 1.0000
13.250 1.3863 0.05721 0.05031 -0.0363 0.0218 1.0000
13.500 1.3865 0.06013 0.05332 -0.0356 0.0214 1.0000
13.750 1.3876 0.06296 0.05626 -0.0348 0.0212 1.0000
14.000 1.3895 0.06576 0.05916 -0.0340 0.0209 1.0000
14.250 1.3916 0.06861 0.06213 -0.0331 0.0207 1.0000
14.500 1.3926 0.07170 0.06538 -0.0325 0.0206 1.0000
14.750 1.3921 0.07509 0.06894 -0.0321 0.0205 1.0000
15.000 1.3890 0.07891 0.07296 -0.0322 0.0205 1.0000
15.250 1.3834 0.08318 0.07744 -0.0327 0.0206 1.0000
15.500 1.3752 0.08797 0.08246 -0.0338 0.0207 1.0000
15.750 1.3644 0.09332 0.08806 -0.0355 0.0208 1.0000
16.000 1.3511 0.09926 0.09425 -0.0378 0.0210 1.0000
16.250 1.3358 0.10581 0.10106 -0.0407 0.0212 1.0000
16.500 1.3178 0.11316 0.10866 -0.0444 0.0214 1.0000
16.750 1.2968 0.12153 0.11729 -0.0492 0.0217 1.0000
17.000 1.2743 0.13065 0.12666 -0.0548 0.0220 1.0000
17.250 1.2505 0.14071 0.13694 -0.0613 0.0223 1.0000
17.500 1.2243 0.15217 0.14861 -0.0691 0.0227 1.0000
17.750 1.1929 0.16617 0.16279 -0.0787 0.0232 1.0000
18.000 1.1449 0.18796 0.18470 -0.0928 0.0243 1.0000
18.250 1.1305 0.19864 0.19535 -0.0985 0.0253 1.0000
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Polar data table (+)
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