GOE 57 AIRFOIL (goe57-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 57 AIRFOIL (goe57-il) Reynolds number: 100,000 Max Cl/Cd: 59.23 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe57-il-100000-n5.txt Download as CSV file: xf-goe57-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 57 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3050 0.09734 0.09270 -0.0244 1.0000 0.0436
-7.250 -0.3115 0.09645 0.09193 -0.0244 1.0000 0.0448
-7.000 -0.3161 0.09578 0.09136 -0.0261 1.0000 0.0455
-6.750 -0.3180 0.09476 0.09041 -0.0283 1.0000 0.0458
-6.500 -0.3156 0.09314 0.08881 -0.0307 1.0000 0.0461
-6.250 -0.2946 0.08964 0.08526 -0.0371 0.9970 0.0462
-6.000 -0.2854 0.08309 0.07876 -0.0359 0.9939 0.0471
-5.750 -0.2709 0.07870 0.07438 -0.0353 0.9898 0.0484
-5.500 -0.2468 0.07488 0.07053 -0.0387 0.9853 0.0509
-5.250 -0.1943 0.07159 0.06701 -0.0538 0.9775 0.0592
-5.000 -0.1444 0.06771 0.06283 -0.0659 0.9705 0.0599
-4.750 -0.1246 0.06199 0.05716 -0.0679 0.9661 0.0608
-4.500 -0.1100 0.05854 0.05377 -0.0670 0.9609 0.0631
-4.250 -0.0796 0.05555 0.05070 -0.0707 0.9552 0.0689
-4.000 -0.0084 0.05249 0.04701 -0.0852 0.9506 0.0745
-3.750 0.0085 0.04808 0.04271 -0.0857 0.9439 0.0759
-3.500 0.0392 0.04500 0.03959 -0.0884 0.9396 0.0782
-3.250 0.0905 0.04291 0.03702 -0.0954 0.9348 0.0892
-3.000 0.1141 0.03976 0.03395 -0.0965 0.9285 0.0918
-2.750 0.1524 0.03722 0.03125 -0.1001 0.9243 0.0945
-2.500 0.2061 0.03234 0.02556 -0.1050 0.9192 0.0589
-2.250 0.2415 0.02993 0.02296 -0.1074 0.9120 0.0576
-2.000 0.2807 0.02762 0.02034 -0.1099 0.9037 0.0568
-1.750 0.3210 0.02546 0.01782 -0.1122 0.8940 0.0566
-1.500 0.3568 0.02412 0.01601 -0.1130 0.8812 0.0596
-1.250 0.3897 0.02258 0.01416 -0.1138 0.8683 0.0606
-0.750 0.4520 0.02040 0.01145 -0.1142 0.8425 0.0599
-0.500 0.4819 0.01945 0.01028 -0.1141 0.8295 0.0600
-0.250 0.5109 0.01853 0.00921 -0.1140 0.8162 0.0604
0.000 0.5391 0.01772 0.00830 -0.1137 0.8020 0.0613
0.250 0.5664 0.01711 0.00763 -0.1132 0.7865 0.0627
0.500 0.5934 0.01662 0.00712 -0.1127 0.7705 0.0648
0.750 0.6199 0.01620 0.00665 -0.1120 0.7521 0.0678
1.000 0.6463 0.01586 0.00622 -0.1112 0.7318 0.0725
1.250 0.6719 0.01561 0.00596 -0.1104 0.7080 0.0810
1.500 0.6987 0.01541 0.00560 -0.1097 0.6824 0.0891
1.750 0.7251 0.01524 0.00528 -0.1089 0.6530 0.0994
2.000 0.7513 0.01515 0.00509 -0.1082 0.6237 0.1217
2.250 0.7746 0.01352 0.00508 -0.1072 0.5986 1.0000
2.500 0.8000 0.01377 0.00505 -0.1064 0.5720 1.0000
2.750 0.8249 0.01405 0.00513 -0.1056 0.5435 1.0000
3.000 0.8493 0.01436 0.00524 -0.1047 0.5125 1.0000
3.500 0.8968 0.01514 0.00561 -0.1029 0.4480 1.0000
3.750 0.9201 0.01559 0.00586 -0.1020 0.4178 1.0000
4.000 0.9432 0.01607 0.00617 -0.1011 0.3897 1.0000
4.250 0.9664 0.01656 0.00652 -0.1003 0.3630 1.0000
4.500 0.9895 0.01706 0.00693 -0.0995 0.3383 1.0000
4.750 1.0123 0.01759 0.00736 -0.0986 0.3164 1.0000
5.000 1.0354 0.01811 0.00781 -0.0979 0.2976 1.0000
5.250 1.0584 0.01863 0.00830 -0.0971 0.2825 1.0000
5.500 1.0813 0.01917 0.00883 -0.0962 0.2705 1.0000
5.750 1.1036 0.01972 0.00933 -0.0954 0.2541 1.0000
6.000 1.1256 0.02028 0.00982 -0.0946 0.2368 1.0000
6.250 1.1467 0.02090 0.01033 -0.0937 0.2183 1.0000
6.500 1.1677 0.02154 0.01092 -0.0927 0.2017 1.0000
6.750 1.1892 0.02214 0.01153 -0.0918 0.1900 1.0000
7.000 1.2103 0.02277 0.01218 -0.0909 0.1771 1.0000
7.250 1.2311 0.02343 0.01288 -0.0899 0.1633 1.0000
7.500 1.2519 0.02409 0.01358 -0.0889 0.1452 1.0000
7.750 1.2705 0.02502 0.01430 -0.0877 0.0770 1.0000
8.000 1.2771 0.02750 0.01630 -0.0850 0.0268 1.0000
8.250 1.2928 0.02882 0.01769 -0.0833 0.0235 1.0000
8.500 1.3090 0.02998 0.01907 -0.0817 0.0223 1.0000
8.750 1.3236 0.03126 0.02057 -0.0798 0.0214 1.0000
9.000 1.3359 0.03265 0.02220 -0.0778 0.0206 1.0000
9.250 1.3450 0.03421 0.02399 -0.0755 0.0196 1.0000
9.750 1.3486 0.03784 0.02811 -0.0694 0.0179 1.0000
10.000 1.3456 0.04003 0.03049 -0.0664 0.0173 1.0000
10.250 1.3412 0.04242 0.03309 -0.0637 0.0170 1.0000
10.500 1.3357 0.04509 0.03594 -0.0614 0.0168 1.0000
10.750 1.3298 0.04799 0.03901 -0.0596 0.0166 1.0000
11.000 1.3239 0.05109 0.04225 -0.0581 0.0165 1.0000
11.250 1.3193 0.05424 0.04553 -0.0568 0.0163 1.0000
11.500 1.3179 0.05720 0.04856 -0.0556 0.0162 1.0000
11.750 1.3194 0.05995 0.05143 -0.0546 0.0161 1.0000
12.000 1.3225 0.06261 0.05420 -0.0535 0.0160 1.0000
12.250 1.3269 0.06525 0.05697 -0.0524 0.0159 1.0000
12.500 1.3303 0.06807 0.05994 -0.0516 0.0157 1.0000
12.750 1.3318 0.07116 0.06321 -0.0510 0.0154 1.0000
13.000 1.3310 0.07459 0.06685 -0.0509 0.0151 1.0000
13.250 1.3288 0.07830 0.07082 -0.0510 0.0148 1.0000
13.500 1.3247 0.08234 0.07507 -0.0514 0.0146 1.0000
13.750 1.3193 0.08666 0.07960 -0.0522 0.0144 1.0000
14.000 1.3126 0.09129 0.08444 -0.0533 0.0142 1.0000
14.250 1.3049 0.09624 0.08962 -0.0548 0.0141 1.0000
14.500 1.2961 0.10155 0.09514 -0.0568 0.0141 1.0000
14.750 1.2864 0.10727 0.10107 -0.0592 0.0141 1.0000
15.000 1.2757 0.11342 0.10743 -0.0623 0.0141 1.0000
15.250 1.2641 0.11999 0.11420 -0.0658 0.0142 1.0000
15.500 1.2519 0.12702 0.12143 -0.0700 0.0142 1.0000
15.750 1.2395 0.13442 0.12902 -0.0745 0.0143 1.0000
16.000 1.2269 0.14230 0.13707 -0.0796 0.0144 1.0000
16.250 1.2144 0.15057 0.14551 -0.0851 0.0145 1.0000
16.500 1.2015 0.15938 0.15447 -0.0910 0.0146 1.0000
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Polar data table (+)
Polar graphs
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