GOE 365 AIRFOIL (goe365-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 365 AIRFOIL (goe365-il) Reynolds number: 50,000 Max Cl/Cd: 34.15 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe365-il-50000-n5.txt Download as CSV file: xf-goe365-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 365 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3028 0.11963 0.11339 -0.0369 1.0000 0.0999
-9.000 -0.3233 0.11962 0.11354 -0.0349 1.0000 0.1002
-8.750 -0.3473 0.11980 0.11387 -0.0325 1.0000 0.1004
-8.500 -0.3211 0.11305 0.10711 -0.0294 1.0000 0.1035
-8.250 -0.3170 0.11039 0.10449 -0.0286 0.9981 0.1064
-8.000 -0.3052 0.10699 0.10109 -0.0325 0.9907 0.1115
-7.750 -0.3124 0.10542 0.09958 -0.0401 0.9780 0.1159
-7.500 -0.3035 0.10116 0.09534 -0.0437 0.9699 0.1182
-7.250 -0.2803 0.09717 0.09132 -0.0422 0.9664 0.1261
-6.750 -0.2598 0.09011 0.08427 -0.0499 0.9504 0.1397
-6.500 -0.2627 0.08802 0.08207 -0.0605 0.9366 0.1499
-6.250 -0.2438 0.08362 0.07777 -0.0558 0.9332 0.1544
-6.000 -0.2389 0.08092 0.07496 -0.0618 0.9231 0.1672
-5.750 -0.2179 0.07717 0.07125 -0.0602 0.9195 0.1737
-5.500 -0.2133 0.07455 0.06859 -0.0613 0.9103 0.1871
-5.250 -0.1946 0.07150 0.06552 -0.0625 0.9054 0.2066
-4.750 -0.1374 0.05967 0.05248 -0.0779 0.8897 0.1019
-4.500 -0.1191 0.05616 0.04856 -0.0778 0.8818 0.0837
-4.250 -0.0957 0.05302 0.04528 -0.0789 0.8763 0.0815
-4.000 -0.0685 0.05016 0.04207 -0.0804 0.8712 0.0811
-3.750 -0.0521 0.04809 0.03972 -0.0795 0.8631 0.0803
-3.500 -0.0205 0.04539 0.03661 -0.0810 0.8585 0.0779
-3.250 -0.0010 0.04355 0.03441 -0.0801 0.8508 0.0762
-3.000 0.0281 0.04162 0.03206 -0.0806 0.8449 0.0758
-2.750 0.0652 0.03978 0.02981 -0.0823 0.8410 0.0776
-2.500 0.0806 0.03884 0.02859 -0.0803 0.8314 0.0781
-2.250 0.1173 0.03726 0.02662 -0.0815 0.8269 0.0777
-2.000 0.1385 0.03639 0.02549 -0.0803 0.8185 0.0775
-1.750 0.1726 0.03524 0.02403 -0.0810 0.8128 0.0779
-1.500 0.2039 0.03441 0.02295 -0.0812 0.8067 0.0801
-1.250 0.2305 0.03384 0.02218 -0.0807 0.7988 0.0825
-1.000 0.2730 0.03289 0.02098 -0.0825 0.7947 0.0840
-0.750 0.2923 0.03269 0.02064 -0.0809 0.7849 0.0849
-0.500 0.3323 0.03180 0.01967 -0.0825 0.7800 0.0870
-0.250 0.3528 0.03162 0.01943 -0.0811 0.7707 0.0897
0.000 0.3875 0.03110 0.01881 -0.0819 0.7647 0.0961
0.250 0.4091 0.03105 0.01867 -0.0807 0.7553 0.1012
0.500 0.4427 0.03055 0.01813 -0.0813 0.7488 0.1088
0.750 0.4644 0.03054 0.01809 -0.0802 0.7391 0.1182
1.000 0.5277 0.02768 0.01772 -0.0865 0.7342 1.0000
1.250 0.5534 0.02788 0.01758 -0.0856 0.7255 1.0000
1.500 0.5810 0.02798 0.01743 -0.0851 0.7168 1.0000
1.750 0.6001 0.02835 0.01763 -0.0835 0.7060 1.0000
2.000 0.6350 0.02818 0.01726 -0.0840 0.6989 1.0000
2.250 0.6502 0.02863 0.01761 -0.0819 0.6865 1.0000
2.500 0.6748 0.02876 0.01762 -0.0810 0.6763 1.0000
2.750 0.7050 0.02863 0.01737 -0.0807 0.6669 1.0000
3.000 0.7220 0.02891 0.01758 -0.0787 0.6536 1.0000
3.250 0.7423 0.02901 0.01762 -0.0770 0.6405 1.0000
3.500 0.7652 0.02895 0.01748 -0.0756 0.6275 1.0000
3.750 0.7902 0.02878 0.01723 -0.0745 0.6148 1.0000
4.000 0.8176 0.02850 0.01688 -0.0736 0.6025 1.0000
4.250 0.8384 0.02850 0.01684 -0.0720 0.5886 1.0000
4.500 0.8577 0.02860 0.01692 -0.0702 0.5743 1.0000
4.750 0.8777 0.02871 0.01700 -0.0686 0.5602 1.0000
5.000 0.8986 0.02882 0.01707 -0.0671 0.5461 1.0000
5.250 0.9199 0.02895 0.01716 -0.0657 0.5321 1.0000
5.500 0.9415 0.02907 0.01726 -0.0644 0.5177 1.0000
5.750 0.9630 0.02925 0.01739 -0.0631 0.5032 1.0000
6.000 0.9841 0.02948 0.01758 -0.0617 0.4884 1.0000
6.250 1.0043 0.02979 0.01785 -0.0603 0.4734 1.0000
6.500 1.0238 0.03017 0.01819 -0.0588 0.4585 1.0000
6.750 1.0425 0.03062 0.01860 -0.0573 0.4436 1.0000
7.000 1.0615 0.03112 0.01908 -0.0559 0.4295 1.0000
7.250 1.0811 0.03166 0.01956 -0.0547 0.4159 1.0000
7.500 1.0978 0.03233 0.02022 -0.0531 0.4023 1.0000
7.750 1.1115 0.03316 0.02107 -0.0513 0.3890 1.0000
8.000 1.1261 0.03401 0.02196 -0.0497 0.3765 1.0000
8.250 1.1430 0.03480 0.02275 -0.0483 0.3652 1.0000
8.500 1.1634 0.03548 0.02341 -0.0474 0.3550 1.0000
8.750 1.1754 0.03663 0.02466 -0.0457 0.3450 1.0000
9.000 1.1964 0.03741 0.02548 -0.0450 0.3366 1.0000
9.250 1.2096 0.03853 0.02671 -0.0436 0.3278 1.0000
9.500 1.2258 0.03951 0.02774 -0.0424 0.3196 1.0000
9.750 1.2394 0.04059 0.02892 -0.0411 0.3116 1.0000
10.000 1.2537 0.04171 0.03014 -0.0398 0.3043 1.0000
10.250 1.2647 0.04298 0.03153 -0.0384 0.2970 1.0000
10.500 1.2807 0.04403 0.03264 -0.0373 0.2904 1.0000
10.750 1.2842 0.04568 0.03447 -0.0354 0.2833 1.0000
11.000 1.3017 0.04653 0.03536 -0.0345 0.2764 1.0000
11.250 1.2986 0.04871 0.03777 -0.0324 0.2701 1.0000
11.500 1.3164 0.04961 0.03872 -0.0316 0.2642 1.0000
11.750 1.3155 0.05188 0.04120 -0.0299 0.2589 1.0000
12.000 1.3152 0.05421 0.04374 -0.0285 0.2540 1.0000
12.250 1.3352 0.05513 0.04475 -0.0279 0.2494 1.0000
12.500 1.3292 0.05809 0.04797 -0.0265 0.2453 1.0000
12.750 1.3113 0.06218 0.05231 -0.0252 0.2410 1.0000
13.000 1.3159 0.06441 0.05470 -0.0244 0.2367 1.0000
13.250 1.3344 0.06548 0.05588 -0.0238 0.2326 1.0000
13.500 1.2607 0.07609 0.06677 -0.0240 0.2285 1.0000
13.750 1.2041 0.08673 0.07753 -0.0263 0.2231 1.0000
14.000 1.2471 0.08401 0.07497 -0.0244 0.2200 1.0000
14.250 1.0877 0.11402 0.10490 -0.0365 0.2070 1.0000
14.500 1.1117 0.11315 0.10417 -0.0350 0.2048 1.0000
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Polar data table (+)
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