GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Reynolds number: 500,000 Max Cl/Cd: 100.02 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe325-il-500000.txt Download as CSV file: xf-goe325-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3385 0.08795 0.08590 -0.0213 1.0000 0.0199
-7.250 -0.3526 0.08670 0.08470 -0.0182 1.0000 0.0203
-7.000 -0.3601 0.08464 0.08268 -0.0179 1.0000 0.0211
-6.750 -0.3203 0.07769 0.07567 -0.0353 0.9955 0.0217
-6.500 -0.2870 0.07168 0.06959 -0.0452 0.9920 0.0218
-6.250 -0.2612 0.06386 0.06172 -0.0539 0.9879 0.0222
-6.000 -0.2337 0.06039 0.05822 -0.0575 0.9854 0.0227
-5.750 -0.1973 0.05660 0.05438 -0.0638 0.9834 0.0236
-5.500 -0.1636 0.05259 0.05029 -0.0698 0.9782 0.0253
-5.250 -0.1076 0.04675 0.04415 -0.0805 0.9736 0.0282
-5.000 -0.0785 0.03860 0.03575 -0.0867 0.9692 0.0290
-4.750 -0.0565 0.03659 0.03370 -0.0875 0.9620 0.0298
-4.500 -0.0298 0.03464 0.03167 -0.0888 0.9565 0.0309
-4.250 -0.0058 0.03258 0.02949 -0.0891 0.9473 0.0337
-4.000 0.0292 0.03087 0.02736 -0.0892 0.9398 0.0369
-3.750 0.0488 0.02525 0.02149 -0.0903 0.9305 0.0388
-3.500 0.0719 0.02400 0.02017 -0.0899 0.9196 0.0401
-3.250 0.0964 0.02279 0.01884 -0.0895 0.9075 0.0428
-3.000 0.1256 0.02074 0.01624 -0.0889 0.8941 0.0490
-2.750 0.1496 0.01896 0.01441 -0.0887 0.8765 0.0507
-2.500 0.1747 0.01798 0.01329 -0.0882 0.8524 0.0528
-2.250 0.2006 0.01719 0.01223 -0.0874 0.8177 0.0568
-2.000 0.2268 0.01607 0.01066 -0.0868 0.7758 0.0635
-1.750 0.2562 0.01296 0.00686 -0.0857 0.7394 0.0439
-1.500 0.2830 0.01204 0.00558 -0.0852 0.6997 0.0427
-1.250 0.3098 0.01154 0.00480 -0.0847 0.6583 0.0429
-1.000 0.3364 0.01122 0.00424 -0.0844 0.6159 0.0437
-0.750 0.3633 0.01086 0.00367 -0.0841 0.5840 0.0439
-0.500 0.3904 0.01062 0.00325 -0.0838 0.5624 0.0446
-0.250 0.4178 0.01043 0.00295 -0.0837 0.5456 0.0456
0.000 0.4454 0.01030 0.00272 -0.0836 0.5315 0.0466
0.250 0.4731 0.01020 0.00254 -0.0835 0.5188 0.0474
0.500 0.5011 0.01002 0.00231 -0.0835 0.5074 0.0497
0.750 0.5290 0.00994 0.00219 -0.0835 0.4965 0.0542
1.000 0.5569 0.00993 0.00213 -0.0835 0.4854 0.0596
1.250 0.5849 0.00977 0.00209 -0.0835 0.4735 0.1155
1.500 0.6064 0.00779 0.00221 -0.0826 0.4619 1.0000
1.750 0.6342 0.00791 0.00222 -0.0825 0.4489 1.0000
2.000 0.6619 0.00805 0.00226 -0.0825 0.4354 1.0000
2.250 0.6894 0.00820 0.00231 -0.0824 0.4213 1.0000
2.500 0.7169 0.00836 0.00237 -0.0823 0.4073 1.0000
2.750 0.7442 0.00854 0.00245 -0.0822 0.3939 1.0000
3.000 0.7714 0.00873 0.00256 -0.0822 0.3818 1.0000
3.500 0.8258 0.00912 0.00282 -0.0820 0.3618 1.0000
3.750 0.8528 0.00934 0.00297 -0.0819 0.3540 1.0000
4.000 0.8800 0.00953 0.00314 -0.0818 0.3468 1.0000
4.250 0.9067 0.00977 0.00333 -0.0817 0.3404 1.0000
4.500 0.9340 0.00994 0.00351 -0.0816 0.3344 1.0000
4.750 0.9606 0.01020 0.00373 -0.0815 0.3286 1.0000
5.000 0.9876 0.01039 0.00393 -0.0814 0.3230 1.0000
5.250 1.0142 0.01060 0.00412 -0.0813 0.3153 1.0000
5.500 1.0410 0.01078 0.00430 -0.0812 0.3068 1.0000
5.750 1.0673 0.01102 0.00453 -0.0810 0.2996 1.0000
6.000 1.0942 0.01118 0.00473 -0.0809 0.2926 1.0000
6.250 1.1203 0.01143 0.00494 -0.0807 0.2843 1.0000
6.500 1.1472 0.01157 0.00514 -0.0807 0.2759 1.0000
6.750 1.1733 0.01178 0.00535 -0.0805 0.2653 1.0000
7.000 1.1993 0.01200 0.00556 -0.0803 0.2528 1.0000
7.250 1.2252 0.01225 0.00579 -0.0801 0.2361 1.0000
7.500 1.2488 0.01277 0.00612 -0.0797 0.1988 1.0000
7.750 1.2557 0.01546 0.00786 -0.0773 0.0520 1.0000
8.000 1.2738 0.01665 0.00887 -0.0760 0.0218 1.0000
8.250 1.2953 0.01737 0.00964 -0.0751 0.0192 1.0000
8.500 1.3154 0.01822 0.01062 -0.0740 0.0173 1.0000
8.750 1.3355 0.01901 0.01151 -0.0729 0.0166 1.0000
9.000 1.3546 0.01983 0.01245 -0.0717 0.0158 1.0000
9.250 1.3720 0.02076 0.01348 -0.0703 0.0148 1.0000
9.500 1.3871 0.02182 0.01463 -0.0686 0.0140 1.0000
9.750 1.3982 0.02311 0.01602 -0.0665 0.0134 1.0000
10.000 1.4033 0.02473 0.01776 -0.0635 0.0129 1.0000
10.250 1.3994 0.02657 0.01973 -0.0592 0.0126 1.0000
10.500 1.3965 0.02846 0.02175 -0.0555 0.0124 1.0000
10.750 1.4026 0.02982 0.02322 -0.0532 0.0123 1.0000
11.000 1.4068 0.03144 0.02494 -0.0509 0.0121 1.0000
11.250 1.4093 0.03330 0.02691 -0.0488 0.0119 1.0000
11.500 1.4110 0.03538 0.02910 -0.0470 0.0117 1.0000
11.750 1.4121 0.03766 0.03150 -0.0455 0.0115 1.0000
12.000 1.4136 0.04006 0.03400 -0.0442 0.0113 1.0000
12.250 1.4152 0.04257 0.03662 -0.0433 0.0111 1.0000
12.500 1.4166 0.04520 0.03935 -0.0426 0.0108 1.0000
12.750 1.4180 0.04793 0.04219 -0.0422 0.0105 1.0000
13.000 1.4188 0.05078 0.04513 -0.0418 0.0103 1.0000
13.250 1.4195 0.05367 0.04812 -0.0414 0.0101 1.0000
13.500 1.4197 0.05670 0.05124 -0.0411 0.0099 1.0000
13.750 1.4195 0.05979 0.05444 -0.0408 0.0098 1.0000
14.000 1.4190 0.06298 0.05773 -0.0406 0.0097 1.0000
14.250 1.4180 0.06628 0.06115 -0.0404 0.0096 1.0000
14.500 1.4161 0.06973 0.06471 -0.0404 0.0096 1.0000
14.750 1.4133 0.07340 0.06852 -0.0405 0.0095 1.0000
15.000 1.4092 0.07735 0.07261 -0.0409 0.0095 1.0000
15.250 1.4036 0.08161 0.07701 -0.0416 0.0094 1.0000
15.500 1.3964 0.08623 0.08178 -0.0427 0.0094 1.0000
15.750 1.3869 0.09140 0.08714 -0.0443 0.0095 1.0000
16.000 1.3749 0.09716 0.09312 -0.0464 0.0096 1.0000
16.250 1.3445 0.10682 0.10316 -0.0513 0.0101 1.0000
16.500 1.3176 0.11625 0.11290 -0.0559 0.0106 1.0000
16.750 1.2975 0.12451 0.12137 -0.0601 0.0109 1.0000
17.000 1.2786 0.13281 0.12985 -0.0647 0.0113 1.0000
17.250 1.2603 0.14139 0.13859 -0.0698 0.0115 1.0000
17.500 1.2417 0.15029 0.14763 -0.0752 0.0119 1.0000
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Polar data table (+)
Polar graphs
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