GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Reynolds number: 200,000 Max Cl/Cd: 72.91 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe325-il-200000.txt Download as CSV file: xf-goe325-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 325 (PFALZ 54) 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 -0.3348 0.09190 0.08864 -0.0238 1.0000 0.0358
-7.250 -0.3424 0.09045 0.08727 -0.0256 1.0000 0.0363
-7.000 -0.3438 0.08841 0.08526 -0.0289 1.0000 0.0366
-6.750 -0.3404 0.08578 0.08264 -0.0318 1.0000 0.0368
-6.500 -0.3345 0.08282 0.07966 -0.0339 1.0000 0.0369
-6.250 -0.3377 0.07749 0.07439 -0.0325 1.0000 0.0375
-6.000 -0.3381 0.07468 0.07164 -0.0281 1.0000 0.0383
-5.750 -0.3347 0.07234 0.06933 -0.0262 1.0000 0.0394
-5.500 -0.3286 0.06977 0.06676 -0.0262 1.0000 0.0407
-5.250 -0.3199 0.06692 0.06390 -0.0274 1.0000 0.0422
-5.000 -0.2620 0.06207 0.05874 -0.0419 0.9962 0.0475
-4.750 -0.2230 0.05484 0.05132 -0.0503 0.9916 0.0488
-4.500 -0.1936 0.05114 0.04766 -0.0531 0.9866 0.0508
-4.250 -0.1471 0.04746 0.04382 -0.0598 0.9811 0.0570
-4.000 -0.0931 0.04188 0.03781 -0.0686 0.9745 0.0624
-3.750 -0.0521 0.03874 0.03465 -0.0732 0.9707 0.0662
-3.500 -0.0061 0.03534 0.03072 -0.0781 0.9631 0.0761
-3.250 0.0331 0.03247 0.02789 -0.0820 0.9588 0.0806
-3.000 0.0793 0.02966 0.02465 -0.0863 0.9533 0.0912
-2.750 0.1306 0.01122 0.00632 -0.0875 0.9222 0.1058
-2.500 0.1604 0.00976 0.00466 -0.0882 0.9106 0.1198
-2.250 0.1861 0.00844 0.00333 -0.0881 0.8966 0.1266
-2.000 0.2118 0.00740 0.00213 -0.0878 0.8785 0.1414
-1.750 0.2589 0.01919 0.01273 -0.0925 0.9011 0.0915
-1.500 0.2906 0.01773 0.01081 -0.0913 0.8837 0.0739
-1.250 0.3179 0.01593 0.00884 -0.0905 0.8604 0.0709
-1.000 0.3458 0.01480 0.00749 -0.0896 0.8319 0.0696
-0.750 0.3730 0.01396 0.00640 -0.0885 0.7962 0.0695
-0.500 0.3991 0.01342 0.00557 -0.0874 0.7555 0.0703
-0.250 0.4249 0.01320 0.00508 -0.0864 0.7159 0.0731
0.000 0.4505 0.01288 0.00455 -0.0856 0.6808 0.0757
0.250 0.4763 0.01256 0.00411 -0.0850 0.6493 0.0790
0.500 0.5025 0.01243 0.00384 -0.0845 0.6219 0.0844
0.750 0.5291 0.01228 0.00358 -0.0841 0.5986 0.0945
1.000 0.5518 0.01071 0.00347 -0.0837 0.5797 0.6257
1.250 0.5774 0.01022 0.00332 -0.0823 0.5616 1.0000
1.500 0.6040 0.01050 0.00338 -0.0820 0.5440 1.0000
1.750 0.6306 0.01079 0.00347 -0.0817 0.5277 1.0000
2.000 0.6573 0.01109 0.00360 -0.0814 0.5124 1.0000
2.250 0.6840 0.01137 0.00375 -0.0812 0.4978 1.0000
2.500 0.7107 0.01165 0.00390 -0.0809 0.4836 1.0000
2.750 0.7373 0.01192 0.00406 -0.0807 0.4703 1.0000
3.000 0.7640 0.01219 0.00422 -0.0805 0.4581 1.0000
3.250 0.7908 0.01242 0.00440 -0.0803 0.4459 1.0000
3.500 0.8176 0.01267 0.00461 -0.0802 0.4349 1.0000
3.750 0.8443 0.01295 0.00481 -0.0800 0.4254 1.0000
4.000 0.8710 0.01321 0.00504 -0.0798 0.4160 1.0000
4.250 0.8977 0.01348 0.00530 -0.0796 0.4068 1.0000
4.750 0.9511 0.01409 0.00586 -0.0793 0.3917 1.0000
5.000 0.9777 0.01447 0.00618 -0.0792 0.3855 1.0000
5.250 1.0043 0.01478 0.00657 -0.0790 0.3787 1.0000
5.500 1.0309 0.01513 0.00690 -0.0789 0.3727 1.0000
5.750 1.0574 0.01552 0.00735 -0.0787 0.3667 1.0000
6.000 1.0839 0.01589 0.00777 -0.0786 0.3612 1.0000
6.250 1.1102 0.01631 0.00817 -0.0784 0.3550 1.0000
6.500 1.1350 0.01649 0.00841 -0.0780 0.3445 1.0000
6.750 1.1596 0.01673 0.00873 -0.0775 0.3340 1.0000
7.000 1.1845 0.01706 0.00905 -0.0771 0.3255 1.0000
7.250 1.2084 0.01722 0.00928 -0.0766 0.3140 1.0000
7.500 1.2324 0.01742 0.00962 -0.0760 0.3034 1.0000
7.750 1.2562 0.01766 0.00997 -0.0754 0.2931 1.0000
8.000 1.2788 0.01774 0.01016 -0.0746 0.2765 1.0000
8.250 1.3007 0.01784 0.01031 -0.0737 0.2521 1.0000
8.500 1.3205 0.01829 0.01064 -0.0726 0.1967 1.0000
8.750 1.3158 0.02182 0.01305 -0.0690 0.0519 1.0000
9.000 1.3282 0.02338 0.01463 -0.0669 0.0373 1.0000
9.250 1.3424 0.02459 0.01593 -0.0651 0.0322 1.0000
9.500 1.3514 0.02613 0.01761 -0.0627 0.0297 1.0000
9.750 1.3609 0.02746 0.01912 -0.0603 0.0285 1.0000
10.000 1.3653 0.02891 0.02072 -0.0573 0.0275 1.0000
10.250 1.3667 0.03052 0.02246 -0.0541 0.0267 1.0000
10.500 1.3666 0.03236 0.02442 -0.0511 0.0260 1.0000
10.750 1.3656 0.03441 0.02658 -0.0485 0.0254 1.0000
11.000 1.3639 0.03670 0.02898 -0.0463 0.0248 1.0000
11.250 1.3607 0.03931 0.03168 -0.0445 0.0241 1.0000
11.500 1.3559 0.04230 0.03475 -0.0427 0.0234 1.0000
11.750 1.3536 0.04531 0.03781 -0.0409 0.0228 1.0000
12.000 1.3583 0.04764 0.04026 -0.0397 0.0225 1.0000
12.250 1.3641 0.04999 0.04273 -0.0384 0.0223 1.0000
12.500 1.3708 0.05237 0.04524 -0.0370 0.0221 1.0000
12.750 1.3783 0.05483 0.04784 -0.0356 0.0220 1.0000
13.000 1.3853 0.05751 0.05069 -0.0343 0.0219 1.0000
13.250 1.3907 0.06052 0.05391 -0.0330 0.0219 1.0000
13.500 1.3936 0.06392 0.05752 -0.0320 0.0220 1.0000
13.750 1.3937 0.06778 0.06160 -0.0313 0.0222 1.0000
14.000 1.3903 0.07207 0.06611 -0.0308 0.0224 1.0000
14.250 1.3831 0.07670 0.07096 -0.0309 0.0225 1.0000
14.500 1.3732 0.08168 0.07617 -0.0314 0.0226 1.0000
14.750 1.3627 0.08715 0.08184 -0.0321 0.0228 1.0000
15.000 1.3515 0.09229 0.08719 -0.0335 0.0229 1.0000
15.250 1.3370 0.09764 0.09273 -0.0358 0.0229 1.0000
15.500 1.3221 0.10321 0.09849 -0.0385 0.0230 1.0000
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Polar data table (+)
Polar graphs
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