GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 326 (PFALZ 55) AIRFOIL (goe326-il) Reynolds number: 500,000 Max Cl/Cd: 104.63 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe326-il-500000.txt Download as CSV file: xf-goe326-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 326 (PFALZ 55) 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3340 0.08727 0.08517 -0.0236 1.0000 0.0207
-7.500 -0.3310 0.08469 0.08264 -0.0244 1.0000 0.0211
-7.250 -0.3281 0.08206 0.08005 -0.0256 1.0000 0.0215
-7.000 -0.3134 0.07835 0.07636 -0.0304 0.9958 0.0224
-6.750 -0.2688 0.07110 0.06902 -0.0487 0.9831 0.0245
-6.500 -0.2331 0.06499 0.06282 -0.0592 0.9708 0.0247
-6.250 -0.2160 0.05912 0.05691 -0.0632 0.9576 0.0252
-6.000 -0.1959 0.05661 0.05435 -0.0645 0.9431 0.0258
-5.750 -0.1750 0.05376 0.05141 -0.0667 0.9270 0.0266
-5.500 -0.1524 0.05057 0.04810 -0.0695 0.9122 0.0278
-5.250 -0.1093 0.04544 0.04261 -0.0767 0.8989 0.0310
-5.000 -0.0892 0.03859 0.03550 -0.0799 0.8866 0.0317
-4.750 -0.0696 0.03682 0.03367 -0.0801 0.8749 0.0324
-4.500 -0.0471 0.03503 0.03177 -0.0805 0.8639 0.0333
-4.250 -0.0221 0.03291 0.02949 -0.0812 0.8534 0.0350
-4.000 0.0145 0.03135 0.02746 -0.0818 0.8425 0.0393
-3.750 0.0363 0.02556 0.02133 -0.0831 0.8328 0.0408
-3.500 0.0608 0.02412 0.01981 -0.0833 0.8226 0.0418
-3.250 0.0865 0.02285 0.01841 -0.0834 0.8115 0.0433
-3.000 0.1137 0.02154 0.01690 -0.0834 0.8010 0.0461
-2.750 0.1450 0.02249 0.01747 -0.0825 0.7907 0.0501
-2.500 0.1695 0.01812 0.01281 -0.0832 0.7813 0.0527
-2.250 0.1964 0.01712 0.01171 -0.0832 0.7712 0.0544
-2.000 0.2239 0.01630 0.01071 -0.0831 0.7616 0.0570
-1.750 0.2530 0.01732 0.01154 -0.0825 0.7510 0.0627
-1.500 0.2820 0.01340 0.00715 -0.0822 0.7420 0.0476
-1.250 0.3099 0.01236 0.00591 -0.0819 0.7321 0.0463
-1.000 0.3378 0.01167 0.00508 -0.0817 0.7214 0.0460
-0.750 0.3657 0.01112 0.00444 -0.0815 0.7100 0.0460
-0.500 0.3934 0.01078 0.00402 -0.0813 0.6983 0.0473
-0.250 0.4210 0.01043 0.00360 -0.0810 0.6855 0.0481
0.000 0.4486 0.01012 0.00323 -0.0808 0.6712 0.0489
0.250 0.4763 0.00991 0.00297 -0.0806 0.6544 0.0498
0.500 0.5036 0.00958 0.00258 -0.0804 0.6345 0.0512
0.750 0.5308 0.00932 0.00225 -0.0802 0.6116 0.0537
1.250 0.5849 0.00931 0.00203 -0.0798 0.5630 0.0616
1.500 0.6119 0.00931 0.00193 -0.0796 0.5442 0.0687
1.750 0.6392 0.00931 0.00190 -0.0794 0.5298 0.0926
2.000 0.6646 0.00742 0.00208 -0.0794 0.5177 1.0000
2.250 0.6917 0.00759 0.00214 -0.0792 0.5054 1.0000
2.500 0.7188 0.00777 0.00222 -0.0790 0.4928 1.0000
2.750 0.7458 0.00795 0.00231 -0.0788 0.4807 1.0000
3.000 0.7732 0.00809 0.00240 -0.0787 0.4696 1.0000
3.250 0.8005 0.00823 0.00250 -0.0786 0.4592 1.0000
3.500 0.8276 0.00840 0.00261 -0.0785 0.4486 1.0000
3.750 0.8546 0.00856 0.00274 -0.0783 0.4373 1.0000
4.000 0.8818 0.00871 0.00286 -0.0782 0.4256 1.0000
4.250 0.9087 0.00888 0.00299 -0.0781 0.4136 1.0000
4.500 0.9355 0.00907 0.00314 -0.0779 0.4003 1.0000
4.750 0.9621 0.00927 0.00330 -0.0777 0.3878 1.0000
5.000 0.9885 0.00949 0.00348 -0.0775 0.3765 1.0000
5.250 1.0149 0.00970 0.00367 -0.0774 0.3639 1.0000
5.500 1.0409 0.00996 0.00388 -0.0771 0.3474 1.0000
5.750 1.0667 0.01022 0.00408 -0.0769 0.3290 1.0000
6.000 1.0925 0.01050 0.00432 -0.0766 0.3135 1.0000
6.250 1.1178 0.01080 0.00456 -0.0763 0.2952 1.0000
6.500 1.1426 0.01118 0.00486 -0.0759 0.2732 1.0000
6.750 1.1672 0.01156 0.00516 -0.0756 0.2498 1.0000
7.000 1.1908 0.01206 0.00553 -0.0751 0.2200 1.0000
7.250 1.2113 0.01292 0.00608 -0.0742 0.1645 1.0000
7.500 1.2303 0.01393 0.00682 -0.0732 0.1230 1.0000
7.750 1.2524 0.01455 0.00738 -0.0725 0.1086 1.0000
8.000 1.2747 0.01512 0.00789 -0.0719 0.0944 1.0000
8.250 1.2960 0.01579 0.00843 -0.0711 0.0711 1.0000
8.500 1.3082 0.01739 0.00965 -0.0691 0.0232 1.0000
8.750 1.3278 0.01816 0.01046 -0.0680 0.0192 1.0000
9.000 1.3476 0.01886 0.01127 -0.0669 0.0179 1.0000
9.250 1.3658 0.01968 0.01219 -0.0656 0.0168 1.0000
9.500 1.3815 0.02067 0.01328 -0.0639 0.0159 1.0000
9.750 1.3930 0.02194 0.01468 -0.0618 0.0150 1.0000
10.000 1.4042 0.02309 0.01594 -0.0596 0.0145 1.0000
10.250 1.4151 0.02404 0.01699 -0.0574 0.0141 1.0000
10.500 1.4225 0.02516 0.01820 -0.0548 0.0136 1.0000
10.750 1.4280 0.02649 0.01962 -0.0522 0.0132 1.0000
11.000 1.4318 0.02804 0.02128 -0.0498 0.0128 1.0000
11.250 1.4346 0.02981 0.02314 -0.0477 0.0125 1.0000
11.500 1.4363 0.03179 0.02523 -0.0459 0.0123 1.0000
11.750 1.4368 0.03402 0.02756 -0.0444 0.0120 1.0000
12.000 1.4360 0.03652 0.03015 -0.0430 0.0118 1.0000
12.250 1.4334 0.03932 0.03304 -0.0419 0.0116 1.0000
12.500 1.4301 0.04231 0.03611 -0.0408 0.0114 1.0000
12.750 1.4261 0.04541 0.03929 -0.0396 0.0112 1.0000
13.000 1.4227 0.04847 0.04242 -0.0380 0.0111 1.0000
13.250 1.4235 0.05118 0.04522 -0.0367 0.0109 1.0000
13.500 1.4251 0.05387 0.04806 -0.0366 0.0108 1.0000
13.750 1.4259 0.05674 0.05106 -0.0366 0.0106 1.0000
14.000 1.4257 0.05977 0.05424 -0.0367 0.0105 1.0000
14.250 1.4246 0.06298 0.05759 -0.0368 0.0103 1.0000
14.500 1.4228 0.06637 0.06111 -0.0371 0.0101 1.0000
14.750 1.4201 0.06992 0.06480 -0.0374 0.0099 1.0000
15.000 1.4168 0.07368 0.06869 -0.0379 0.0098 1.0000
15.250 1.4127 0.07765 0.07280 -0.0385 0.0097 1.0000
15.500 1.4075 0.08185 0.07714 -0.0393 0.0097 1.0000
15.750 1.4012 0.08631 0.08175 -0.0404 0.0096 1.0000
16.000 1.3939 0.09107 0.08666 -0.0418 0.0095 1.0000
16.250 1.3854 0.09615 0.09189 -0.0435 0.0095 1.0000
16.500 1.3758 0.10153 0.09743 -0.0455 0.0095 1.0000
16.750 1.3651 0.10726 0.10332 -0.0478 0.0095 1.0000
17.000 1.3535 0.11333 0.10955 -0.0505 0.0095 1.0000
17.250 1.3410 0.11978 0.11617 -0.0537 0.0096 1.0000
17.500 1.3279 0.12653 0.12308 -0.0572 0.0096 1.0000
17.750 1.3140 0.13368 0.13040 -0.0612 0.0096 1.0000
18.000 1.3001 0.14115 0.13802 -0.0655 0.0097 1.0000
18.250 1.2852 0.14916 0.14619 -0.0704 0.0098 1.0000
18.500 1.2702 0.15751 0.15470 -0.0757 0.0099 1.0000
18.750 1.2547 0.16636 0.16369 -0.0814 0.0100 1.0000
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