GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Reynolds number: 100,000 Max Cl/Cd: 56.33 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe326-il-100000.txt Download as CSV file: xf-goe326-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3413 0.10484 0.10001 -0.0210 1.0000 0.0610
-8.250 -0.3442 0.10368 0.09894 -0.0248 1.0000 0.0621
-8.000 -0.3471 0.10253 0.09789 -0.0301 1.0000 0.0626
-7.750 -0.3429 0.10063 0.09603 -0.0368 1.0000 0.0629
-7.500 -0.3352 0.09356 0.08903 -0.0302 1.0000 0.0641
-7.250 -0.3258 0.08964 0.08514 -0.0270 1.0000 0.0661
-7.000 -0.3210 0.08687 0.08243 -0.0267 1.0000 0.0685
-6.750 -0.3199 0.08449 0.08013 -0.0272 1.0000 0.0710
-6.500 -0.3219 0.08251 0.07821 -0.0281 1.0000 0.0735
-6.250 -0.3262 0.08158 0.07732 -0.0315 1.0000 0.0758
-6.000 -0.3241 0.08149 0.07707 -0.0380 1.0000 0.0768
-5.750 -0.3288 0.07661 0.07235 -0.0337 1.0000 0.0778
-5.500 -0.3316 0.07366 0.06949 -0.0294 1.0000 0.0790
-5.250 -0.3309 0.07133 0.06721 -0.0271 1.0000 0.0810
-5.000 -0.3260 0.06900 0.06488 -0.0267 1.0000 0.0839
-4.750 -0.2892 0.06677 0.06219 -0.0387 0.9990 0.0919
-4.500 -0.2732 0.06138 0.05702 -0.0377 0.9946 0.0949
-4.250 -0.2238 0.05721 0.05255 -0.0475 0.9875 0.1080
-4.000 -0.1932 0.05357 0.04893 -0.0500 0.9819 0.1152
-3.750 -0.1517 0.04976 0.04494 -0.0562 0.9744 0.1275
-3.500 -0.1100 0.04650 0.04153 -0.0616 0.9678 0.1445
-3.250 -0.0674 0.04351 0.03829 -0.0672 0.9600 0.1699
-3.000 -0.0267 0.04102 0.03562 -0.0716 0.9524 0.1987
-2.750 0.0110 0.03823 0.03282 -0.0749 0.9451 0.2300
-2.000 0.1081 0.03137 0.02621 -0.0782 0.9212 0.4123
-1.750 0.2231 0.02706 0.01932 -0.0931 0.9159 0.1360
-1.500 0.2642 0.02477 0.01677 -0.0951 0.9067 0.1266
-1.250 0.3093 0.02311 0.01470 -0.0970 0.8987 0.1162
-1.000 0.3437 0.02190 0.01320 -0.0972 0.8862 0.1116
-0.750 0.3765 0.02094 0.01203 -0.0971 0.8733 0.1100
-0.500 0.4069 0.02013 0.01117 -0.0967 0.8599 0.1132
-0.250 0.4357 0.01947 0.01045 -0.0959 0.8458 0.1179
0.000 0.4633 0.01884 0.00976 -0.0948 0.8313 0.1204
0.250 0.4894 0.01814 0.00911 -0.0936 0.8164 0.1249
0.500 0.5151 0.01766 0.00861 -0.0922 0.8012 0.1331
0.750 0.5416 0.01725 0.00819 -0.0911 0.7860 0.1525
1.000 0.5722 0.01480 0.00778 -0.0907 0.7714 1.0000
1.250 0.5985 0.01488 0.00743 -0.0894 0.7557 1.0000
1.500 0.6243 0.01499 0.00729 -0.0883 0.7399 1.0000
1.750 0.6501 0.01513 0.00725 -0.0873 0.7241 1.0000
2.000 0.6758 0.01530 0.00727 -0.0864 0.7084 1.0000
2.250 0.7016 0.01549 0.00731 -0.0856 0.6928 1.0000
2.500 0.7274 0.01569 0.00740 -0.0848 0.6774 1.0000
2.750 0.7532 0.01589 0.00750 -0.0841 0.6622 1.0000
3.000 0.7791 0.01609 0.00763 -0.0835 0.6473 1.0000
3.250 0.8050 0.01629 0.00776 -0.0828 0.6326 1.0000
3.500 0.8309 0.01651 0.00791 -0.0822 0.6181 1.0000
3.750 0.8568 0.01673 0.00809 -0.0816 0.6038 1.0000
4.000 0.8827 0.01698 0.00828 -0.0810 0.5895 1.0000
4.250 0.9085 0.01724 0.00847 -0.0803 0.5747 1.0000
4.500 0.9341 0.01752 0.00868 -0.0797 0.5597 1.0000
4.750 0.9595 0.01787 0.00900 -0.0791 0.5450 1.0000
5.000 0.9849 0.01829 0.00940 -0.0785 0.5311 1.0000
5.250 1.0102 0.01874 0.00983 -0.0780 0.5174 1.0000
5.500 1.0351 0.01918 0.01026 -0.0774 0.5033 1.0000
5.750 1.0601 0.01964 0.01076 -0.0768 0.4903 1.0000
6.000 1.0852 0.02010 0.01123 -0.0762 0.4778 1.0000
6.250 1.1099 0.02049 0.01164 -0.0756 0.4645 1.0000
6.500 1.1346 0.02087 0.01206 -0.0749 0.4514 1.0000
6.750 1.1582 0.02125 0.01256 -0.0742 0.4378 1.0000
7.000 1.1817 0.02162 0.01305 -0.0734 0.4241 1.0000
7.250 1.2049 0.02197 0.01351 -0.0726 0.4100 1.0000
7.500 1.2276 0.02220 0.01382 -0.0715 0.3937 1.0000
7.750 1.2480 0.02238 0.01410 -0.0702 0.3733 1.0000
8.000 1.2670 0.02250 0.01423 -0.0686 0.3493 1.0000
8.250 1.2843 0.02280 0.01462 -0.0669 0.3226 1.0000
8.500 1.3011 0.02330 0.01516 -0.0653 0.2952 1.0000
8.750 1.3168 0.02399 0.01589 -0.0635 0.2668 1.0000
9.000 1.3307 0.02479 0.01665 -0.0617 0.2374 1.0000
9.250 1.3444 0.02571 0.01755 -0.0599 0.2120 1.0000
9.500 1.3576 0.02673 0.01856 -0.0581 0.1919 1.0000
9.750 1.3692 0.02782 0.01965 -0.0562 0.1690 1.0000
10.000 1.3765 0.02919 0.02099 -0.0540 0.1463 1.0000
10.250 1.3770 0.03101 0.02270 -0.0511 0.1245 1.0000
10.500 1.3726 0.03315 0.02484 -0.0477 0.1008 1.0000
10.750 1.3659 0.03569 0.02734 -0.0446 0.0786 1.0000
11.000 1.3607 0.03830 0.02993 -0.0422 0.0663 1.0000
11.250 1.3546 0.04114 0.03272 -0.0403 0.0603 1.0000
11.500 1.3525 0.04383 0.03554 -0.0387 0.0558 1.0000
11.750 1.3500 0.04666 0.03844 -0.0375 0.0526 1.0000
12.000 1.3453 0.04979 0.04156 -0.0363 0.0502 1.0000
12.250 1.3466 0.05248 0.04438 -0.0351 0.0478 1.0000
12.500 1.3483 0.05517 0.04721 -0.0342 0.0454 1.0000
12.750 1.3492 0.05797 0.05011 -0.0334 0.0433 1.0000
13.000 1.3516 0.06067 0.05283 -0.0324 0.0417 1.0000
13.250 1.3613 0.06298 0.05512 -0.0302 0.0404 1.0000
13.500 1.3672 0.06580 0.05818 -0.0291 0.0398 1.0000
13.750 1.3709 0.06902 0.06164 -0.0281 0.0392 1.0000
14.000 1.3704 0.07275 0.06564 -0.0275 0.0389 1.0000
14.250 1.3655 0.07700 0.07017 -0.0274 0.0387 1.0000
14.500 1.3564 0.08180 0.07523 -0.0279 0.0386 1.0000
14.750 1.3432 0.08712 0.08083 -0.0291 0.0386 1.0000
15.000 1.3272 0.09299 0.08696 -0.0309 0.0386 1.0000
15.250 1.3090 0.09943 0.09365 -0.0335 0.0387 1.0000
15.500 1.2892 0.10649 0.10095 -0.0369 0.0390 1.0000
15.750 1.2680 0.11421 0.10888 -0.0410 0.0392 1.0000
16.000 1.2459 0.12260 0.11747 -0.0459 0.0396 1.0000
16.250 1.2235 0.13161 0.12664 -0.0514 0.0399 1.0000
16.500 1.2014 0.14119 0.13636 -0.0574 0.0403 1.0000
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Polar data table (+)
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