GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Reynolds number: 100,000 Max Cl/Cd: 55.28 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe325-il-100000-n5.txt Download as CSV file: xf-goe325-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3299 0.10460 0.09988 -0.0275 1.0000 0.0414
-8.000 -0.3344 0.10272 0.09810 -0.0281 1.0000 0.0416
-7.750 -0.3369 0.10047 0.09592 -0.0292 1.0000 0.0417
-7.500 -0.3367 0.09787 0.09338 -0.0307 1.0000 0.0418
-7.250 -0.3351 0.09507 0.09062 -0.0321 1.0000 0.0418
-7.000 -0.3323 0.09209 0.08768 -0.0335 1.0000 0.0419
-6.750 -0.3281 0.08896 0.08456 -0.0349 1.0000 0.0419
-6.500 -0.3237 0.08536 0.08102 -0.0359 1.0000 0.0420
-6.250 -0.3267 0.08087 0.07661 -0.0304 1.0000 0.0432
-6.000 -0.3244 0.07841 0.07420 -0.0270 1.0000 0.0451
-5.750 -0.3197 0.07594 0.07177 -0.0268 1.0000 0.0477
-5.500 -0.2728 0.07141 0.06697 -0.0430 0.9946 0.0545
-5.250 -0.2322 0.06610 0.06139 -0.0521 0.9882 0.0549
-5.000 -0.2064 0.06013 0.05540 -0.0560 0.9830 0.0555
-4.750 -0.1888 0.05696 0.05233 -0.0556 0.9780 0.0592
-4.500 -0.1288 0.05338 0.04803 -0.0674 0.9704 0.0681
-4.250 -0.1060 0.04638 0.04120 -0.0690 0.9659 0.0504
-4.000 -0.0665 0.04204 0.03653 -0.0740 0.9587 0.0512
-3.750 -0.0236 0.03778 0.03188 -0.0790 0.9532 0.0509
-3.500 0.0154 0.03406 0.02774 -0.0824 0.9447 0.0499
-3.250 0.0606 0.03079 0.02390 -0.0863 0.9373 0.0529
-3.000 0.0959 0.02814 0.02082 -0.0879 0.9248 0.0527
-2.750 0.1300 0.02591 0.01818 -0.0890 0.9113 0.0527
-2.500 0.1626 0.02406 0.01593 -0.0897 0.8968 0.0531
-2.250 0.1946 0.02268 0.01413 -0.0901 0.8816 0.0555
-1.750 0.2556 0.02011 0.01111 -0.0905 0.8447 0.0568
-1.500 0.2874 0.01904 0.00982 -0.0907 0.8234 0.0573
-1.250 0.3181 0.01813 0.00874 -0.0906 0.7980 0.0581
-1.000 0.3486 0.01737 0.00778 -0.0905 0.7699 0.0594
-0.750 0.3777 0.01677 0.00699 -0.0901 0.7401 0.0611
-0.500 0.4055 0.01631 0.00635 -0.0896 0.7101 0.0634
-0.250 0.4324 0.01604 0.00586 -0.0890 0.6803 0.0671
0.000 0.4588 0.01581 0.00552 -0.0885 0.6514 0.0735
0.250 0.4851 0.01568 0.00520 -0.0879 0.6250 0.0796
0.500 0.5115 0.01556 0.00488 -0.0873 0.6016 0.0872
0.750 0.5385 0.01545 0.00464 -0.0870 0.5810 0.1076
1.000 0.5620 0.01333 0.00455 -0.0859 0.5638 1.0000
1.250 0.5886 0.01360 0.00449 -0.0855 0.5476 1.0000
1.500 0.6152 0.01387 0.00451 -0.0852 0.5325 1.0000
1.750 0.6417 0.01415 0.00458 -0.0848 0.5185 1.0000
2.000 0.6683 0.01444 0.00470 -0.0845 0.5053 1.0000
2.250 0.6947 0.01473 0.00484 -0.0843 0.4926 1.0000
2.500 0.7211 0.01502 0.00499 -0.0840 0.4803 1.0000
2.750 0.7475 0.01530 0.00518 -0.0837 0.4682 1.0000
3.000 0.7739 0.01557 0.00539 -0.0835 0.4563 1.0000
3.250 0.8002 0.01586 0.00561 -0.0832 0.4453 1.0000
3.500 0.8264 0.01616 0.00585 -0.0829 0.4351 1.0000
3.750 0.8525 0.01646 0.00611 -0.0826 0.4249 1.0000
4.000 0.8787 0.01676 0.00639 -0.0824 0.4150 1.0000
4.250 0.9046 0.01709 0.00667 -0.0821 0.4069 1.0000
4.500 0.9307 0.01742 0.00704 -0.0819 0.3985 1.0000
4.750 0.9566 0.01778 0.00738 -0.0816 0.3913 1.0000
5.000 0.9825 0.01814 0.00777 -0.0813 0.3836 1.0000
5.250 1.0081 0.01853 0.00817 -0.0810 0.3771 1.0000
5.500 1.0339 0.01892 0.00864 -0.0808 0.3703 1.0000
5.750 1.0596 0.01935 0.00907 -0.0805 0.3652 1.0000
6.000 1.0853 0.01980 0.00966 -0.0803 0.3593 1.0000
6.250 1.1108 0.02025 0.01019 -0.0800 0.3538 1.0000
6.500 1.1362 0.02073 0.01071 -0.0797 0.3490 1.0000
6.750 1.1614 0.02122 0.01138 -0.0794 0.3435 1.0000
7.000 1.1867 0.02172 0.01203 -0.0791 0.3387 1.0000
7.250 1.2104 0.02215 0.01258 -0.0785 0.3302 1.0000
7.500 1.2329 0.02249 0.01298 -0.0777 0.3191 1.0000
7.750 1.2540 0.02279 0.01337 -0.0768 0.3048 1.0000
8.000 1.2740 0.02307 0.01381 -0.0757 0.2876 1.0000
8.250 1.2947 0.02342 0.01437 -0.0746 0.2716 1.0000
8.500 1.3139 0.02379 0.01488 -0.0734 0.2496 1.0000
8.750 1.3311 0.02437 0.01547 -0.0720 0.2085 1.0000
9.000 1.3251 0.02738 0.01739 -0.0686 0.0762 1.0000
9.500 1.3327 0.03172 0.02153 -0.0632 0.0296 1.0000
9.750 1.3384 0.03341 0.02336 -0.0607 0.0264 1.0000
10.000 1.3384 0.03523 0.02534 -0.0577 0.0247 1.0000
10.250 1.3372 0.03725 0.02758 -0.0549 0.0237 1.0000
10.500 1.3351 0.03945 0.03001 -0.0525 0.0228 1.0000
10.750 1.3306 0.04202 0.03280 -0.0505 0.0218 1.0000
11.000 1.3241 0.04504 0.03603 -0.0491 0.0211 1.0000
11.250 1.3157 0.04861 0.03981 -0.0486 0.0204 1.0000
11.500 1.3060 0.05277 0.04418 -0.0489 0.0199 1.0000
11.750 1.2953 0.05749 0.04909 -0.0499 0.0195 1.0000
12.000 1.2842 0.06262 0.05440 -0.0513 0.0192 1.0000
12.250 1.2733 0.06786 0.05981 -0.0529 0.0189 1.0000
12.500 1.2632 0.07296 0.06506 -0.0543 0.0187 1.0000
12.750 1.2543 0.07775 0.06998 -0.0555 0.0185 1.0000
13.000 1.2474 0.08204 0.07437 -0.0561 0.0182 1.0000
13.250 1.2437 0.08565 0.07807 -0.0563 0.0179 1.0000
13.500 1.2443 0.08827 0.08075 -0.0555 0.0175 1.0000
13.750 1.2515 0.08941 0.08191 -0.0531 0.0169 1.0000
14.000 1.2591 0.09094 0.08348 -0.0510 0.0165 1.0000
14.250 1.2607 0.09419 0.08691 -0.0511 0.0161 1.0000
14.500 1.2608 0.09777 0.09068 -0.0516 0.0157 1.0000
14.750 1.2596 0.10165 0.09480 -0.0524 0.0153 1.0000
15.000 1.2575 0.10577 0.09911 -0.0534 0.0150 1.0000
15.250 1.2547 0.11013 0.10367 -0.0546 0.0148 1.0000
15.500 1.2504 0.11488 0.10862 -0.0561 0.0146 1.0000
15.750 1.2445 0.12008 0.11402 -0.0582 0.0146 1.0000
16.000 1.2371 0.12576 0.11990 -0.0608 0.0145 1.0000
16.250 1.2284 0.13193 0.12627 -0.0640 0.0145 1.0000
16.500 1.2186 0.13860 0.13315 -0.0678 0.0145 1.0000
16.750 1.2078 0.14580 0.14054 -0.0721 0.0146 1.0000
17.000 1.1958 0.15364 0.14856 -0.0770 0.0146 1.0000
17.250 1.1832 0.16208 0.15717 -0.0824 0.0147 1.0000
17.500 1.1696 0.17133 0.16657 -0.0885 0.0149 1.0000
17.750 1.1554 0.18153 0.17690 -0.0952 0.0151 1.0000
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