GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 330 (PFALZ 59) AIRFOIL (goe330-il) Reynolds number: 50,000 Max Cl/Cd: 38.4 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe330-il-50000-n5.txt Download as CSV file: xf-goe330-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 330 (PFALZ 59) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3141 0.11389 0.10781 -0.0270 1.0000 0.0886
-7.750 -0.3331 0.11375 0.10780 -0.0248 1.0000 0.0893
-7.500 -0.3511 0.11346 0.10764 -0.0237 1.0000 0.0899
-7.250 -0.3500 0.11123 0.10549 -0.0290 0.9956 0.0907
-7.000 -0.3316 0.10543 0.09965 -0.0241 0.9947 0.0946
-6.750 -0.3149 0.10173 0.09593 -0.0282 0.9879 0.0987
-6.500 -0.2952 0.09883 0.09297 -0.0407 0.9768 0.1038
-6.250 -0.2787 0.09428 0.08843 -0.0440 0.9703 0.1056
-6.000 -0.2619 0.09032 0.08447 -0.0431 0.9654 0.1102
-5.500 -0.2223 0.08315 0.07722 -0.0524 0.9505 0.1250
-5.000 -0.1789 0.07615 0.07011 -0.0612 0.9354 0.1401
-4.750 -0.1556 0.07293 0.06675 -0.0673 0.9263 0.1514
-4.500 -0.1282 0.06960 0.06332 -0.0717 0.9199 0.1661
-4.000 -0.0887 0.06408 0.05776 -0.0734 0.9056 0.2025
-3.500 0.0182 0.05228 0.04463 -0.0933 0.8916 0.0881
-3.250 0.0536 0.04915 0.04120 -0.0966 0.8844 0.0858
-3.000 0.0916 0.04626 0.03792 -0.0999 0.8758 0.0858
-2.750 0.1274 0.04355 0.03479 -0.1023 0.8662 0.0833
-2.500 0.1733 0.04064 0.03123 -0.1059 0.8594 0.0801
-2.250 0.2063 0.03879 0.02883 -0.1069 0.8491 0.0787
-2.000 0.2495 0.03678 0.02635 -0.1096 0.8436 0.0785
-1.750 0.2750 0.03559 0.02505 -0.1095 0.8333 0.0808
-1.500 0.3155 0.03412 0.02327 -0.1116 0.8280 0.0844
-1.250 0.3416 0.03324 0.02212 -0.1112 0.8172 0.0855
-1.000 0.3824 0.03190 0.02043 -0.1128 0.8119 0.0866
-0.750 0.4066 0.03128 0.01958 -0.1119 0.8003 0.0879
-0.500 0.4381 0.03052 0.01855 -0.1119 0.7915 0.0898
-0.250 0.4720 0.02964 0.01755 -0.1124 0.7830 0.0933
0.000 0.4988 0.02920 0.01702 -0.1119 0.7720 0.1004
0.250 0.5358 0.02831 0.01605 -0.1128 0.7650 0.1098
0.750 0.5867 0.02762 0.01524 -0.1114 0.7409 0.1335
1.000 0.6193 0.02669 0.01468 -0.1120 0.7316 0.1962
1.500 0.6738 0.02481 0.01410 -0.1107 0.7081 1.0000
1.750 0.7002 0.02486 0.01392 -0.1100 0.6959 1.0000
2.000 0.7288 0.02483 0.01368 -0.1096 0.6845 1.0000
2.250 0.7607 0.02466 0.01331 -0.1096 0.6743 1.0000
2.500 0.7864 0.02479 0.01330 -0.1089 0.6611 1.0000
2.750 0.8128 0.02493 0.01332 -0.1083 0.6484 1.0000
3.000 0.8401 0.02507 0.01332 -0.1079 0.6361 1.0000
3.250 0.8690 0.02517 0.01328 -0.1077 0.6246 1.0000
3.500 0.8977 0.02532 0.01333 -0.1075 0.6131 1.0000
3.750 0.9213 0.02573 0.01368 -0.1067 0.6001 1.0000
4.000 0.9456 0.02614 0.01404 -0.1060 0.5880 1.0000
4.250 0.9719 0.02647 0.01433 -0.1057 0.5771 1.0000
4.500 0.9970 0.02687 0.01469 -0.1051 0.5663 1.0000
4.750 1.0181 0.02747 0.01531 -0.1042 0.5548 1.0000
5.000 1.0423 0.02793 0.01577 -0.1036 0.5448 1.0000
5.250 1.0671 0.02837 0.01623 -0.1031 0.5353 1.0000
5.500 1.0870 0.02904 0.01696 -0.1020 0.5249 1.0000
5.750 1.1115 0.02946 0.01738 -0.1014 0.5156 1.0000
6.000 1.1337 0.02994 0.01792 -0.1005 0.5053 1.0000
6.250 1.1526 0.03052 0.01855 -0.0991 0.4939 1.0000
6.500 1.1739 0.03094 0.01900 -0.0980 0.4827 1.0000
6.750 1.1986 0.03121 0.01924 -0.0972 0.4722 1.0000
7.000 1.2163 0.03188 0.02004 -0.0958 0.4612 1.0000
7.250 1.2361 0.03256 0.02081 -0.0947 0.4518 1.0000
7.500 1.2611 0.03305 0.02135 -0.0942 0.4436 1.0000
7.750 1.2770 0.03400 0.02247 -0.0927 0.4347 1.0000
8.000 1.3045 0.03446 0.02301 -0.0926 0.4272 1.0000
8.250 1.3164 0.03563 0.02441 -0.0906 0.4182 1.0000
8.500 1.3423 0.03619 0.02504 -0.0903 0.4105 1.0000
8.750 1.3525 0.03743 0.02653 -0.0882 0.4014 1.0000
9.000 1.3740 0.03819 0.02745 -0.0874 0.3934 1.0000
9.250 1.3846 0.03942 0.02893 -0.0853 0.3845 1.0000
9.500 1.4021 0.04040 0.03008 -0.0841 0.3768 1.0000
9.750 1.4113 0.04169 0.03161 -0.0819 0.3682 1.0000
10.000 1.4159 0.04280 0.03290 -0.0789 0.3580 1.0000
10.250 1.4210 0.04341 0.03362 -0.0758 0.3452 1.0000
10.500 1.4197 0.04419 0.03446 -0.0721 0.3313 1.0000
10.750 1.4107 0.04583 0.03627 -0.0684 0.3189 1.0000
11.000 1.4011 0.04798 0.03861 -0.0653 0.3077 1.0000
11.250 1.3962 0.04991 0.04068 -0.0628 0.2966 1.0000
11.500 1.3927 0.05180 0.04270 -0.0607 0.2852 1.0000
11.750 1.3834 0.05456 0.04564 -0.0588 0.2736 1.0000
12.000 1.3714 0.05804 0.04933 -0.0575 0.2625 1.0000
12.250 1.3625 0.06140 0.05289 -0.0565 0.2519 1.0000
12.500 1.3523 0.06504 0.05668 -0.0559 0.2397 1.0000
12.750 1.3402 0.06918 0.06096 -0.0557 0.2262 1.0000
13.000 1.3287 0.07349 0.06541 -0.0557 0.2128 1.0000
13.250 1.3165 0.07807 0.07007 -0.0561 0.1976 1.0000
13.500 1.3047 0.08249 0.07440 -0.0565 0.1766 1.0000
13.750 1.2906 0.08767 0.07959 -0.0573 0.1574 1.0000
14.000 1.2747 0.09373 0.08580 -0.0588 0.1399 1.0000
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Polar data table (+)
Polar graphs
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