GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Reynolds number: 1,000,000 Max Cl/Cd: 121.42 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe325-il-1000000.txt Download as CSV file: xf-goe325-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2625 0.09246 0.09099 -0.0283 1.0000 0.0131
-9.000 -0.2635 0.08909 0.08764 -0.0285 1.0000 0.0131
-8.750 -0.3524 0.09856 0.09701 -0.0213 1.0000 0.0131
-8.500 -0.3478 0.09497 0.09343 -0.0234 1.0000 0.0131
-8.250 -0.3446 0.09157 0.09005 -0.0251 1.0000 0.0131
-8.000 -0.3505 0.08921 0.08772 -0.0242 1.0000 0.0131
-7.750 -0.3448 0.08396 0.08248 -0.0280 0.9967 0.0134
-7.500 -0.3235 0.08062 0.07915 -0.0323 0.9946 0.0136
-7.250 -0.3021 0.07710 0.07561 -0.0377 0.9906 0.0139
-7.000 -0.2104 0.05702 0.05558 -0.0494 0.9653 0.0168
-6.750 -0.2031 0.05243 0.05096 -0.0533 0.9570 0.0169
-6.500 -0.1928 0.04720 0.04569 -0.0580 0.9491 0.0169
-6.250 -0.1805 0.04198 0.04041 -0.0622 0.9423 0.0170
-6.000 -0.1875 0.05209 0.05032 -0.0710 0.9529 0.0170
-5.500 -0.1430 0.03662 0.03443 -0.0816 0.9389 0.0173
-5.250 -0.1266 0.04149 0.03947 -0.0780 0.9312 0.0184
-5.000 -0.0925 0.03809 0.03588 -0.0805 0.9241 0.0217
-4.750 -0.0660 0.03293 0.03048 -0.0826 0.9157 0.0218
-4.500 -0.0421 0.01942 0.01603 -0.0861 0.9082 0.0224
-4.250 -0.0174 0.02280 0.01969 -0.0855 0.8948 0.0232
-4.000 0.0065 0.02421 0.02117 -0.0851 0.8773 0.0248
-3.750 0.0365 0.02365 0.02037 -0.0842 0.8552 0.0281
-3.500 0.0611 0.01668 0.01269 -0.0851 0.8287 0.0263
-3.250 0.0880 0.01504 0.01050 -0.0847 0.7873 0.0289
-3.000 0.1145 0.01399 0.00908 -0.0844 0.7443 0.0288
-2.750 0.1417 0.01282 0.00756 -0.0842 0.7090 0.0287
-2.500 0.1688 0.01132 0.00572 -0.0842 0.6731 0.0296
-2.250 0.1958 0.01097 0.00512 -0.0841 0.6232 0.0305
-2.000 0.2229 0.01063 0.00453 -0.0840 0.5776 0.0309
-1.750 0.2507 0.01026 0.00398 -0.0840 0.5528 0.0312
-1.500 0.2786 0.00990 0.00351 -0.0839 0.5369 0.0315
-1.250 0.3066 0.00959 0.00309 -0.0839 0.5243 0.0318
-1.000 0.3347 0.00938 0.00281 -0.0839 0.5134 0.0326
-0.500 0.3913 0.00898 0.00230 -0.0840 0.4943 0.0343
-0.250 0.4195 0.00885 0.00211 -0.0840 0.4856 0.0352
0.000 0.4479 0.00875 0.00196 -0.0841 0.4762 0.0359
0.250 0.4763 0.00867 0.00184 -0.0841 0.4665 0.0364
0.500 0.5045 0.00863 0.00174 -0.0842 0.4559 0.0369
0.750 0.5329 0.00854 0.00158 -0.0843 0.4443 0.0382
1.000 0.5612 0.00849 0.00149 -0.0843 0.4321 0.0418
1.250 0.5894 0.00850 0.00146 -0.0844 0.4187 0.0467
1.500 0.6176 0.00845 0.00148 -0.0844 0.4040 0.0951
1.750 0.6390 0.00654 0.00168 -0.0837 0.3904 1.0000
2.000 0.6669 0.00670 0.00173 -0.0837 0.3756 1.0000
2.250 0.6947 0.00685 0.00179 -0.0837 0.3627 1.0000
2.500 0.7224 0.00701 0.00186 -0.0837 0.3519 1.0000
2.750 0.7501 0.00717 0.00194 -0.0837 0.3425 1.0000
3.000 0.7780 0.00729 0.00203 -0.0837 0.3352 1.0000
3.250 0.8056 0.00746 0.00214 -0.0837 0.3277 1.0000
3.500 0.8335 0.00758 0.00223 -0.0837 0.3222 1.0000
3.750 0.8611 0.00773 0.00235 -0.0837 0.3163 1.0000
4.000 0.8887 0.00789 0.00248 -0.0837 0.3109 1.0000
4.250 0.9165 0.00801 0.00259 -0.0838 0.3059 1.0000
4.500 0.9436 0.00821 0.00273 -0.0837 0.2985 1.0000
4.750 0.9714 0.00832 0.00285 -0.0837 0.2921 1.0000
5.000 0.9985 0.00851 0.00300 -0.0837 0.2847 1.0000
5.250 1.0260 0.00863 0.00312 -0.0837 0.2778 1.0000
5.500 1.0531 0.00882 0.00327 -0.0837 0.2706 1.0000
5.750 1.0804 0.00895 0.00342 -0.0837 0.2640 1.0000
6.000 1.1072 0.00917 0.00359 -0.0836 0.2541 1.0000
6.250 1.1341 0.00934 0.00375 -0.0836 0.2444 1.0000
6.500 1.1606 0.00957 0.00395 -0.0835 0.2317 1.0000
6.750 1.1862 0.00991 0.00419 -0.0833 0.2106 1.0000
7.000 1.2018 0.01163 0.00519 -0.0818 0.0973 1.0000
7.250 1.2175 0.01333 0.00640 -0.0803 0.0191 1.0000
7.500 1.2421 0.01375 0.00686 -0.0799 0.0158 1.0000
7.750 1.2660 0.01425 0.00740 -0.0794 0.0141 1.0000
8.000 1.2886 0.01490 0.00815 -0.0786 0.0125 1.0000
8.250 1.3124 0.01536 0.00865 -0.0781 0.0120 1.0000
8.500 1.3355 0.01585 0.00919 -0.0775 0.0113 1.0000
8.750 1.3579 0.01641 0.00981 -0.0768 0.0106 1.0000
9.000 1.3791 0.01706 0.01052 -0.0759 0.0100 1.0000
9.250 1.3972 0.01801 0.01155 -0.0746 0.0094 1.0000
9.500 1.4106 0.01935 0.01303 -0.0726 0.0089 1.0000
9.750 1.4305 0.01996 0.01370 -0.0716 0.0087 1.0000
10.000 1.4482 0.02072 0.01454 -0.0703 0.0084 1.0000
10.250 1.4640 0.02158 0.01548 -0.0687 0.0081 1.0000
10.500 1.4783 0.02248 0.01645 -0.0669 0.0078 1.0000
10.750 1.4914 0.02337 0.01741 -0.0650 0.0075 1.0000
11.000 1.5011 0.02425 0.01834 -0.0625 0.0072 1.0000
11.250 1.5090 0.02524 0.01940 -0.0600 0.0070 1.0000
11.500 1.5134 0.02653 0.02076 -0.0573 0.0068 1.0000
11.750 1.5120 0.02832 0.02265 -0.0542 0.0066 1.0000
12.000 1.5049 0.03075 0.02518 -0.0512 0.0064 1.0000
12.250 1.4890 0.03426 0.02884 -0.0482 0.0063 1.0000
12.500 1.4834 0.03722 0.03191 -0.0467 0.0062 1.0000
12.750 1.4877 0.03943 0.03422 -0.0461 0.0061 1.0000
13.000 1.4891 0.04211 0.03701 -0.0458 0.0061 1.0000
13.250 1.4895 0.04506 0.04006 -0.0458 0.0060 1.0000
13.500 1.4883 0.04833 0.04344 -0.0460 0.0059 1.0000
13.750 1.4859 0.05183 0.04706 -0.0464 0.0058 1.0000
14.000 1.4826 0.05554 0.05087 -0.0469 0.0058 1.0000
14.250 1.4787 0.05940 0.05484 -0.0475 0.0057 1.0000
14.500 1.4741 0.06336 0.05891 -0.0482 0.0056 1.0000
14.750 1.4690 0.06743 0.06309 -0.0489 0.0056 1.0000
15.000 1.4636 0.07157 0.06734 -0.0497 0.0055 1.0000
15.250 1.4577 0.07581 0.07169 -0.0506 0.0054 1.0000
15.500 1.4514 0.08016 0.07615 -0.0516 0.0054 1.0000
15.750 1.4447 0.08464 0.08074 -0.0527 0.0053 1.0000
16.000 1.4380 0.08923 0.08543 -0.0540 0.0052 1.0000
16.250 1.4310 0.09393 0.09024 -0.0555 0.0052 1.0000
16.500 1.4236 0.09880 0.09522 -0.0570 0.0051 1.0000
16.750 1.4161 0.10380 0.10033 -0.0588 0.0051 1.0000
17.000 1.4079 0.10896 0.10560 -0.0606 0.0050 1.0000
17.250 1.4000 0.11419 0.11094 -0.0628 0.0050 1.0000
17.500 1.3917 0.11961 0.11647 -0.0651 0.0049 1.0000
17.750 1.3837 0.12510 0.12206 -0.0676 0.0049 1.0000
18.000 1.3751 0.13079 0.12787 -0.0703 0.0048 1.0000
18.250 1.3671 0.13645 0.13363 -0.0731 0.0048 1.0000
18.500 1.3580 0.14247 0.13977 -0.0763 0.0048 1.0000
18.750 1.3497 0.14852 0.14591 -0.0797 0.0047 1.0000
19.000 1.3399 0.15501 0.15252 -0.0834 0.0047 1.0000
19.250 1.3305 0.16161 0.15924 -0.0873 0.0047 1.0000
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