GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.16 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe325-il-1000000-n5.txt Download as CSV file: xf-goe325-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3648 0.10013 0.09858 -0.0205 1.0000 0.0049
-9.000 -0.3593 0.09566 0.09411 -0.0235 0.9927 0.0051
-7.500 -0.3571 0.01379 0.00980 -0.0917 0.9356 0.0108
-7.250 -0.3306 0.01292 0.00878 -0.0916 0.9308 0.0119
-7.000 -0.3032 0.01293 0.00881 -0.0914 0.9257 0.0131
-6.750 -0.2761 0.01273 0.00857 -0.0912 0.9204 0.0142
-6.500 -0.2495 0.01198 0.00764 -0.0910 0.9121 0.0153
-6.250 -0.2222 0.01218 0.00787 -0.0907 0.9003 0.0159
-6.000 -0.1949 0.01263 0.00836 -0.0902 0.8844 0.0165
-5.750 -0.1682 0.01297 0.00867 -0.0897 0.8583 0.0171
-5.500 -0.1423 0.01307 0.00858 -0.0891 0.8143 0.0177
-5.250 -0.1162 0.01306 0.00830 -0.0886 0.7640 0.0186
-5.000 -0.0891 0.01290 0.00792 -0.0885 0.7295 0.0195
-4.750 -0.0617 0.01276 0.00759 -0.0884 0.7013 0.0202
-4.500 -0.0342 0.01273 0.00739 -0.0883 0.6680 0.0206
-4.250 -0.0069 0.01284 0.00728 -0.0882 0.6209 0.0209
-4.000 0.0199 0.01190 0.00597 -0.0883 0.5762 0.0218
-3.750 0.0475 0.01161 0.00551 -0.0883 0.5498 0.0226
-3.500 0.0754 0.01142 0.00520 -0.0884 0.5317 0.0231
-3.250 0.1034 0.01126 0.00494 -0.0884 0.5191 0.0237
-3.000 0.1316 0.01109 0.00470 -0.0885 0.5100 0.0243
-2.750 0.1598 0.01080 0.00431 -0.0885 0.5014 0.0248
-2.500 0.1880 0.01051 0.00394 -0.0886 0.4931 0.0252
-2.250 0.2162 0.01023 0.00356 -0.0886 0.4843 0.0255
-2.000 0.2445 0.00997 0.00323 -0.0887 0.4771 0.0258
-1.750 0.2727 0.00973 0.00292 -0.0888 0.4691 0.0261
-1.500 0.3010 0.00951 0.00264 -0.0888 0.4609 0.0263
-1.250 0.3293 0.00936 0.00241 -0.0889 0.4514 0.0266
-1.000 0.3576 0.00923 0.00223 -0.0890 0.4413 0.0271
-0.750 0.3859 0.00910 0.00203 -0.0890 0.4318 0.0273
-0.500 0.4142 0.00900 0.00186 -0.0891 0.4207 0.0275
-0.250 0.4424 0.00895 0.00173 -0.0891 0.4073 0.0279
0.000 0.4705 0.00894 0.00164 -0.0892 0.3920 0.0285
0.250 0.4985 0.00897 0.00160 -0.0892 0.3772 0.0291
0.500 0.5265 0.00901 0.00158 -0.0893 0.3645 0.0295
0.750 0.5546 0.00903 0.00155 -0.0893 0.3539 0.0302
1.000 0.5827 0.00904 0.00151 -0.0894 0.3449 0.0319
1.500 0.6387 0.00914 0.00152 -0.0895 0.3287 0.0353
2.000 0.6946 0.00924 0.00162 -0.0895 0.3155 0.0432
2.250 0.7226 0.00923 0.00170 -0.0896 0.3101 0.0887
2.750 0.7724 0.00755 0.00203 -0.0890 0.3016 1.0000
3.000 0.8003 0.00766 0.00211 -0.0891 0.2972 1.0000
3.250 0.8281 0.00780 0.00220 -0.0891 0.2928 1.0000
3.500 0.8559 0.00791 0.00230 -0.0891 0.2890 1.0000
3.750 0.8837 0.00803 0.00240 -0.0892 0.2848 1.0000
4.000 0.9114 0.00816 0.00251 -0.0892 0.2806 1.0000
4.250 0.9389 0.00831 0.00264 -0.0892 0.2756 1.0000
4.500 0.9664 0.00844 0.00275 -0.0892 0.2693 1.0000
4.750 0.9935 0.00863 0.00289 -0.0892 0.2607 1.0000
5.000 1.0209 0.00877 0.00303 -0.0892 0.2546 1.0000
5.250 1.0479 0.00897 0.00319 -0.0891 0.2456 1.0000
5.500 1.0746 0.00918 0.00335 -0.0891 0.2344 1.0000
5.750 1.1013 0.00940 0.00354 -0.0890 0.2230 1.0000
6.000 1.1271 0.00973 0.00377 -0.0888 0.2051 1.0000
6.250 1.1511 0.01029 0.00412 -0.0884 0.1677 1.0000
6.500 1.1651 0.01224 0.00538 -0.0867 0.0493 1.0000
6.750 1.1875 0.01301 0.00598 -0.0861 0.0163 1.0000
7.000 1.2123 0.01340 0.00639 -0.0857 0.0126 1.0000
7.250 1.2373 0.01375 0.00676 -0.0854 0.0106 1.0000
7.500 1.2622 0.01408 0.00713 -0.0850 0.0097 1.0000
7.750 1.2865 0.01448 0.00755 -0.0846 0.0087 1.0000
8.000 1.3099 0.01498 0.00809 -0.0841 0.0074 1.0000
8.250 1.3340 0.01535 0.00849 -0.0837 0.0070 1.0000
8.500 1.3575 0.01577 0.00895 -0.0832 0.0064 1.0000
8.750 1.3805 0.01623 0.00944 -0.0826 0.0059 1.0000
9.000 1.4027 0.01675 0.00999 -0.0819 0.0055 1.0000
9.250 1.4232 0.01743 0.01074 -0.0809 0.0050 1.0000
9.500 1.4447 0.01795 0.01132 -0.0802 0.0049 1.0000
9.750 1.4655 0.01851 0.01193 -0.0793 0.0046 1.0000
10.000 1.4857 0.01909 0.01256 -0.0784 0.0043 1.0000
10.250 1.5052 0.01968 0.01320 -0.0773 0.0041 1.0000
10.500 1.5239 0.02030 0.01387 -0.0762 0.0038 1.0000
10.750 1.5409 0.02103 0.01464 -0.0749 0.0036 1.0000
11.000 1.5549 0.02192 0.01562 -0.0731 0.0034 1.0000
11.250 1.5645 0.02295 0.01674 -0.0706 0.0033 1.0000
11.500 1.5740 0.02380 0.01768 -0.0681 0.0032 1.0000
11.750 1.5825 0.02477 0.01873 -0.0656 0.0032 1.0000
12.000 1.5892 0.02590 0.01996 -0.0631 0.0031 1.0000
12.250 1.5950 0.02716 0.02132 -0.0608 0.0030 1.0000
12.500 1.5992 0.02862 0.02287 -0.0586 0.0029 1.0000
12.750 1.6024 0.03027 0.02463 -0.0565 0.0028 1.0000
13.000 1.6041 0.03218 0.02664 -0.0547 0.0028 1.0000
13.250 1.6044 0.03439 0.02896 -0.0533 0.0027 1.0000
13.500 1.6042 0.03687 0.03155 -0.0523 0.0027 1.0000
13.750 1.6018 0.03985 0.03466 -0.0518 0.0026 1.0000
14.000 1.5987 0.04319 0.03811 -0.0518 0.0026 1.0000
14.250 1.5934 0.04708 0.04213 -0.0523 0.0025 1.0000
14.500 1.5877 0.05123 0.04640 -0.0532 0.0025 1.0000
14.750 1.5798 0.05594 0.05124 -0.0545 0.0025 1.0000
15.000 1.5704 0.06097 0.05639 -0.0560 0.0024 1.0000
15.250 1.5585 0.06630 0.06183 -0.0575 0.0024 1.0000
15.500 1.5455 0.07177 0.06743 -0.0590 0.0024 1.0000
15.750 1.5310 0.07748 0.07325 -0.0605 0.0024 1.0000
16.000 1.5167 0.08319 0.07907 -0.0621 0.0024 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 325 (PFALZ 54) AIRFOIL (goe325-il)