GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 329 (PFALZ 58) AIRFOIL (goe329-il) Reynolds number: 100,000 Max Cl/Cd: 56.23 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe329-il-100000-n5.txt Download as CSV file: xf-goe329-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 329 (PFALZ 58) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.2646 0.10895 0.10416 -0.0372 1.0000 0.0438
-8.750 -0.2763 0.10817 0.10349 -0.0362 1.0000 0.0442
-8.500 -0.2943 0.10796 0.10340 -0.0335 1.0000 0.0444
-8.250 -0.2930 0.10592 0.10140 -0.0406 0.9903 0.0447
-8.000 -0.2706 0.10009 0.09556 -0.0372 0.9912 0.0459
-7.750 -0.2529 0.09636 0.09181 -0.0401 0.9856 0.0475
-7.500 -0.2376 0.09285 0.08831 -0.0443 0.9774 0.0492
-7.250 -0.2180 0.08898 0.08441 -0.0510 0.9687 0.0513
-7.000 -0.1876 0.08493 0.08025 -0.0682 0.9564 0.0533
-6.750 -0.1664 0.08010 0.07539 -0.0719 0.9495 0.0539
-6.500 -0.1488 0.07633 0.07164 -0.0709 0.9430 0.0554
-6.250 -0.1261 0.07289 0.06815 -0.0742 0.9341 0.0583
-6.000 -0.0849 0.06953 0.06444 -0.0897 0.9215 0.0634
-5.750 -0.0644 0.06479 0.05973 -0.0914 0.9154 0.0643
-5.500 -0.0501 0.06174 0.05670 -0.0906 0.9058 0.0656
-5.250 -0.0254 0.05863 0.05351 -0.0930 0.8993 0.0682
-5.000 0.0172 0.05674 0.05106 -0.1022 0.8883 0.0750
-4.750 0.0348 0.05225 0.04667 -0.1027 0.8815 0.0764
-4.500 0.0514 0.04967 0.04413 -0.1022 0.8720 0.0790
-4.000 0.1079 0.04446 0.03850 -0.1071 0.8547 0.0910
-3.750 0.1311 0.04223 0.03621 -0.1077 0.8455 0.0947
-3.500 0.1638 0.04006 0.03368 -0.1103 0.8369 0.1051
-3.250 0.1936 0.03962 0.03289 -0.1113 0.8263 0.1184
-3.000 0.2159 0.03603 0.02936 -0.1119 0.8177 0.1218
-2.750 0.2435 0.03476 0.02790 -0.1124 0.8068 0.1329
-2.500 0.2859 0.03103 0.02336 -0.1133 0.7974 0.0739
-2.250 0.3168 0.02846 0.02045 -0.1136 0.7880 0.0614
-2.000 0.3449 0.02672 0.01846 -0.1137 0.7758 0.0575
-1.750 0.3763 0.02539 0.01656 -0.1135 0.7641 0.0529
-1.500 0.4042 0.02409 0.01507 -0.1134 0.7519 0.0519
-1.250 0.4326 0.02299 0.01372 -0.1133 0.7393 0.0511
-1.000 0.4606 0.02204 0.01255 -0.1130 0.7252 0.0504
-0.750 0.4883 0.02127 0.01156 -0.1126 0.7102 0.0509
-0.500 0.5160 0.02065 0.01070 -0.1122 0.6944 0.0521
-0.250 0.5434 0.02005 0.00990 -0.1118 0.6782 0.0525
0.000 0.5704 0.01946 0.00917 -0.1113 0.6611 0.0524
0.250 0.5972 0.01897 0.00856 -0.1109 0.6433 0.0525
0.500 0.6237 0.01857 0.00804 -0.1104 0.6254 0.0526
0.750 0.6500 0.01824 0.00761 -0.1099 0.6080 0.0530
1.000 0.6758 0.01801 0.00728 -0.1093 0.5911 0.0535
1.250 0.7016 0.01779 0.00696 -0.1088 0.5751 0.0547
1.500 0.7276 0.01772 0.00679 -0.1084 0.5599 0.0579
1.750 0.7541 0.01775 0.00667 -0.1081 0.5461 0.0613
2.000 0.7807 0.01784 0.00657 -0.1078 0.5337 0.0635
2.250 0.8074 0.01791 0.00653 -0.1076 0.5218 0.0671
2.500 0.8340 0.01805 0.00657 -0.1073 0.5104 0.0736
2.750 0.8592 0.01701 0.00683 -0.1075 0.5007 0.6249
3.250 0.9057 0.01695 0.00700 -0.1050 0.4830 1.0000
3.500 0.9319 0.01728 0.00719 -0.1048 0.4748 1.0000
3.750 0.9580 0.01762 0.00744 -0.1046 0.4667 1.0000
4.000 0.9841 0.01797 0.00769 -0.1043 0.4592 1.0000
4.250 1.0101 0.01833 0.00800 -0.1042 0.4522 1.0000
4.500 1.0361 0.01870 0.00833 -0.1040 0.4456 1.0000
4.750 1.0622 0.01910 0.00864 -0.1038 0.4400 1.0000
5.000 1.0878 0.01948 0.00907 -0.1036 0.4333 1.0000
5.250 1.1136 0.01988 0.00944 -0.1034 0.4276 1.0000
5.500 1.1392 0.02030 0.00986 -0.1033 0.4221 1.0000
5.750 1.1646 0.02073 0.01036 -0.1031 0.4165 1.0000
6.000 1.1903 0.02117 0.01081 -0.1029 0.4119 1.0000
6.250 1.2158 0.02163 0.01130 -0.1027 0.4073 1.0000
6.500 1.2404 0.02210 0.01190 -0.1024 0.4019 1.0000
6.750 1.2655 0.02257 0.01242 -0.1022 0.3972 1.0000
7.000 1.2914 0.02307 0.01292 -0.1021 0.3935 1.0000
7.250 1.3151 0.02361 0.01366 -0.1017 0.3889 1.0000
7.500 1.3393 0.02415 0.01435 -0.1013 0.3844 1.0000
7.750 1.3641 0.02467 0.01495 -0.1011 0.3804 1.0000
8.000 1.3885 0.02522 0.01561 -0.1008 0.3764 1.0000
8.250 1.4089 0.02573 0.01635 -0.0998 0.3691 1.0000
8.500 1.4290 0.02603 0.01671 -0.0987 0.3596 1.0000
8.750 1.4459 0.02628 0.01704 -0.0970 0.3474 1.0000
9.000 1.4606 0.02666 0.01760 -0.0951 0.3348 1.0000
9.250 1.4740 0.02706 0.01816 -0.0931 0.3210 1.0000
9.500 1.4855 0.02753 0.01874 -0.0907 0.3056 1.0000
9.750 1.4947 0.02812 0.01944 -0.0881 0.2884 1.0000
10.000 1.4994 0.02888 0.02028 -0.0849 0.2667 1.0000
10.250 1.4977 0.03003 0.02140 -0.0810 0.2317 1.0000
10.750 1.4566 0.03626 0.02672 -0.0721 0.1056 1.0000
11.000 1.4358 0.04029 0.03055 -0.0690 0.0767 1.0000
11.250 1.4215 0.04406 0.03431 -0.0669 0.0581 1.0000
11.500 1.4090 0.04792 0.03825 -0.0655 0.0489 1.0000
11.750 1.3974 0.05196 0.04240 -0.0646 0.0444 1.0000
12.000 1.3850 0.05636 0.04695 -0.0642 0.0416 1.0000
12.250 1.3707 0.06131 0.05203 -0.0644 0.0398 1.0000
12.500 1.3557 0.06663 0.05751 -0.0649 0.0385 1.0000
12.750 1.3419 0.07208 0.06315 -0.0658 0.0374 1.0000
13.000 1.3278 0.07775 0.06901 -0.0669 0.0363 1.0000
13.250 1.3144 0.08347 0.07489 -0.0682 0.0354 1.0000
13.500 1.3016 0.08915 0.08072 -0.0695 0.0344 1.0000
13.750 1.2895 0.09473 0.08642 -0.0708 0.0335 1.0000
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Polar data table (+)
Polar graphs
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