GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 325 (PFALZ 54) AIRFOIL (goe325-il) Reynolds number: 100,000 Max Cl/Cd: 53.75 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe325-il-100000.txt Download as CSV file: xf-goe325-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3329 0.09216 0.08762 -0.0226 1.0000 0.0661
-7.000 -0.3334 0.08976 0.08528 -0.0226 1.0000 0.0678
-6.750 -0.3340 0.08739 0.08297 -0.0232 1.0000 0.0698
-6.500 -0.3340 0.08519 0.08083 -0.0253 1.0000 0.0721
-6.250 -0.3277 0.08413 0.07971 -0.0344 1.0000 0.0741
-6.000 -0.3206 0.08058 0.07613 -0.0375 1.0000 0.0748
-5.750 -0.3209 0.07596 0.07167 -0.0317 1.0000 0.0762
-5.500 -0.3171 0.07307 0.06883 -0.0288 1.0000 0.0786
-5.250 -0.3094 0.07040 0.06617 -0.0289 1.0000 0.0826
-5.000 -0.2799 0.06798 0.06340 -0.0402 1.0000 0.0892
-4.750 -0.2793 0.06373 0.05934 -0.0362 1.0000 0.0908
-4.500 -0.2718 0.06096 0.05663 -0.0344 1.0000 0.0937
-4.250 -0.2543 0.05833 0.05389 -0.0364 1.0000 0.1002
-4.000 -0.2330 0.05484 0.05024 -0.0399 1.0000 0.1055
-3.750 -0.2219 0.05235 0.04780 -0.0389 1.0000 0.1100
-3.500 -0.1984 0.04958 0.04483 -0.0419 1.0000 0.1205
-3.250 -0.1696 0.04706 0.04211 -0.0452 0.9983 0.1341
-3.000 -0.1186 0.04307 0.03800 -0.0520 0.9895 0.1507
-2.750 -0.0635 0.03977 0.03447 -0.0595 0.9799 0.1793
-2.500 -0.0146 0.03689 0.03154 -0.0652 0.9709 0.2243
-1.500 0.2211 0.02483 0.01713 -0.0868 0.9304 0.1231
-1.250 0.2704 0.02282 0.01466 -0.0896 0.9172 0.1097
-1.000 0.3153 0.02132 0.01271 -0.0913 0.9018 0.1049
-0.750 0.3552 0.01984 0.01121 -0.0927 0.8845 0.1099
-0.500 0.3878 0.01869 0.00994 -0.0923 0.8599 0.1114
-0.250 0.4202 0.01765 0.00879 -0.0918 0.8341 0.1137
0.000 0.4509 0.01682 0.00782 -0.0910 0.8058 0.1179
0.250 0.4788 0.01595 0.00696 -0.0900 0.7762 0.1269
0.500 0.5057 0.01547 0.00633 -0.0888 0.7465 0.1479
0.750 0.5316 0.01290 0.00568 -0.0872 0.7201 1.0000
1.000 0.5583 0.01316 0.00542 -0.0862 0.6932 1.0000
1.250 0.5843 0.01346 0.00539 -0.0854 0.6674 1.0000
1.500 0.6102 0.01378 0.00543 -0.0847 0.6431 1.0000
1.750 0.6363 0.01412 0.00548 -0.0841 0.6218 1.0000
2.000 0.6623 0.01449 0.00564 -0.0836 0.6005 1.0000
2.250 0.6885 0.01490 0.00584 -0.0831 0.5816 1.0000
2.500 0.7148 0.01535 0.00607 -0.0826 0.5643 1.0000
2.750 0.7411 0.01584 0.00636 -0.0823 0.5484 1.0000
3.000 0.7676 0.01634 0.00675 -0.0820 0.5338 1.0000
3.250 0.7939 0.01685 0.00716 -0.0817 0.5200 1.0000
3.500 0.8202 0.01736 0.00762 -0.0815 0.5072 1.0000
3.750 0.8465 0.01789 0.00809 -0.0812 0.4956 1.0000
4.000 0.8731 0.01842 0.00857 -0.0810 0.4858 1.0000
4.250 0.8994 0.01894 0.00910 -0.0808 0.4760 1.0000
4.500 0.9255 0.01950 0.00969 -0.0806 0.4670 1.0000
4.750 0.9522 0.02001 0.01015 -0.0804 0.4591 1.0000
5.000 0.9777 0.02058 0.01087 -0.0802 0.4503 1.0000
5.250 1.0046 0.02114 0.01138 -0.0801 0.4440 1.0000
5.500 1.0297 0.02180 0.01223 -0.0799 0.4365 1.0000
5.750 1.0562 0.02237 0.01284 -0.0797 0.4305 1.0000
6.000 1.0811 0.02308 0.01372 -0.0794 0.4237 1.0000
6.250 1.1069 0.02371 0.01445 -0.0792 0.4176 1.0000
6.500 1.1329 0.02445 0.01527 -0.0790 0.4128 1.0000
6.750 1.1566 0.02532 0.01644 -0.0787 0.4067 1.0000
7.000 1.1827 0.02598 0.01718 -0.0785 0.4016 1.0000
7.250 1.2058 0.02676 0.01819 -0.0780 0.3944 1.0000
7.500 1.2315 0.02674 0.01813 -0.0773 0.3836 1.0000
7.750 1.2563 0.02653 0.01792 -0.0765 0.3703 1.0000
8.000 1.2794 0.02635 0.01776 -0.0755 0.3559 1.0000
8.250 1.3015 0.02623 0.01772 -0.0743 0.3412 1.0000
8.500 1.3201 0.02600 0.01767 -0.0727 0.3229 1.0000
8.750 1.3377 0.02555 0.01731 -0.0708 0.3009 1.0000
9.000 1.3512 0.02514 0.01714 -0.0683 0.2720 1.0000
9.250 1.3531 0.02557 0.01724 -0.0645 0.1515 1.0000
9.500 1.3394 0.02959 0.02036 -0.0601 0.0753 1.0000
9.750 1.3378 0.03211 0.02292 -0.0567 0.0637 1.0000
10.000 1.3321 0.03443 0.02534 -0.0529 0.0590 1.0000
10.250 1.3291 0.03649 0.02759 -0.0495 0.0557 1.0000
10.500 1.3242 0.03882 0.03007 -0.0467 0.0531 1.0000
10.750 1.3173 0.04152 0.03286 -0.0443 0.0510 1.0000
11.000 1.3082 0.04463 0.03600 -0.0422 0.0493 1.0000
11.250 1.3082 0.04718 0.03866 -0.0407 0.0473 1.0000
11.500 1.3109 0.04961 0.04122 -0.0394 0.0453 1.0000
11.750 1.3173 0.05180 0.04350 -0.0378 0.0437 1.0000
12.000 1.3291 0.05370 0.04542 -0.0359 0.0423 1.0000
12.250 1.3466 0.05553 0.04726 -0.0339 0.0410 1.0000
12.500 1.3721 0.05766 0.04942 -0.0321 0.0400 1.0000
12.750 1.4101 0.06194 0.05375 -0.0315 0.0386 1.0000
13.000 1.4043 0.06489 0.05700 -0.0299 0.0383 1.0000
13.250 1.3971 0.06822 0.06063 -0.0288 0.0380 1.0000
13.500 1.3884 0.07196 0.06470 -0.0281 0.0377 1.0000
13.750 1.3785 0.07615 0.06916 -0.0279 0.0377 1.0000
14.000 1.3671 0.08075 0.07403 -0.0282 0.0377 1.0000
14.250 1.3543 0.08578 0.07930 -0.0289 0.0379 1.0000
14.500 1.3398 0.09119 0.08495 -0.0302 0.0381 1.0000
14.750 1.3247 0.09697 0.09095 -0.0320 0.0383 1.0000
15.000 1.3095 0.10315 0.09733 -0.0341 0.0385 1.0000
15.250 1.2942 0.10920 0.10360 -0.0368 0.0388 1.0000
15.500 1.2741 0.11540 0.11003 -0.0410 0.0391 1.0000
15.750 1.2503 0.12297 0.11784 -0.0467 0.0395 1.0000
16.000 1.2178 0.13343 0.12855 -0.0550 0.0402 1.0000
16.250 1.1291 0.16243 0.15788 -0.0773 0.0462 1.0000
16.500 1.1143 0.17276 0.16821 -0.0831 0.0477 1.0000
16.750 1.1115 0.17944 0.17487 -0.0859 0.0486 1.0000
17.000 0.8111 0.17402 0.16964 -0.0642 0.0580 1.0000
17.250 0.8140 0.17744 0.17307 -0.0647 0.0594 1.0000
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Polar data table (+)
Polar graphs
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