GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Reynolds number: 200,000 Max Cl/Cd: 76.57 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe174-il-200000-n5.txt Download as CSV file: xf-goe174-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 174 (ALBATROS 5020) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2811 0.09963 0.09630 -0.0299 1.0000 0.0227
-8.000 -0.2842 0.09736 0.09411 -0.0295 1.0000 0.0227
-7.750 -0.2901 0.09534 0.09217 -0.0283 1.0000 0.0227
-7.500 -0.2798 0.09161 0.08848 -0.0319 0.9961 0.0227
-7.250 -0.2569 0.08666 0.08352 -0.0390 0.9880 0.0228
-6.750 -0.2206 0.07827 0.07514 -0.0455 0.9678 0.0235
-6.500 -0.2005 0.07544 0.07229 -0.0477 0.9562 0.0252
-6.250 -0.1691 0.07073 0.06754 -0.0571 0.9420 0.0278
-6.000 -0.1247 0.06434 0.06101 -0.0715 0.9285 0.0287
-5.750 -0.0868 0.05859 0.05512 -0.0806 0.9174 0.0288
-5.250 -0.0318 0.05124 0.04764 -0.0882 0.8944 0.0315
-5.000 0.0157 0.04601 0.04212 -0.0979 0.8803 0.0364
-4.750 0.0402 0.04177 0.03773 -0.1007 0.8652 0.0318
-4.500 0.0737 0.03787 0.03357 -0.1048 0.8487 0.0337
-4.250 0.1069 0.03330 0.02863 -0.1085 0.8312 0.0334
-4.000 0.1400 0.02793 0.02271 -0.1115 0.8128 0.0319
-3.750 0.1688 0.02524 0.01958 -0.1125 0.7922 0.0340
-3.500 0.1976 0.02258 0.01639 -0.1131 0.7726 0.0343
-3.250 0.2259 0.02058 0.01390 -0.1133 0.7539 0.0345
-3.000 0.2539 0.01927 0.01216 -0.1132 0.7343 0.0357
-2.750 0.2816 0.01840 0.01087 -0.1130 0.7141 0.0366
-2.250 0.3360 0.01669 0.00846 -0.1124 0.6783 0.0369
-2.000 0.3632 0.01605 0.00756 -0.1120 0.6633 0.0371
-1.750 0.3901 0.01520 0.00648 -0.1118 0.6501 0.0378
-1.500 0.4170 0.01460 0.00578 -0.1116 0.6383 0.0394
-1.250 0.4441 0.01422 0.00529 -0.1113 0.6276 0.0401
-1.000 0.4711 0.01390 0.00486 -0.1110 0.6173 0.0403
-0.750 0.4983 0.01362 0.00450 -0.1107 0.6068 0.0407
-0.500 0.5255 0.01339 0.00423 -0.1105 0.5969 0.0412
0.000 0.5800 0.01311 0.00382 -0.1101 0.5776 0.0428
0.250 0.6072 0.01303 0.00367 -0.1099 0.5675 0.0438
0.750 0.6614 0.01295 0.00347 -0.1094 0.5453 0.0485
1.000 0.6885 0.01292 0.00341 -0.1092 0.5341 0.0515
1.250 0.7154 0.01293 0.00338 -0.1089 0.5225 0.0559
1.500 0.7419 0.01269 0.00348 -0.1088 0.5093 0.1888
1.750 0.7682 0.01270 0.00352 -0.1084 0.4941 0.2331
2.000 0.7918 0.01130 0.00362 -0.1076 0.4782 1.0000
2.250 0.8178 0.01150 0.00368 -0.1072 0.4615 1.0000
2.500 0.8437 0.01171 0.00375 -0.1068 0.4456 1.0000
2.750 0.8694 0.01195 0.00386 -0.1063 0.4306 1.0000
3.000 0.8951 0.01220 0.00400 -0.1059 0.4168 1.0000
3.250 0.9206 0.01246 0.00415 -0.1055 0.4038 1.0000
3.500 0.9460 0.01273 0.00433 -0.1050 0.3915 1.0000
3.750 0.9715 0.01300 0.00454 -0.1047 0.3804 1.0000
4.000 0.9970 0.01328 0.00475 -0.1043 0.3715 1.0000
4.250 1.0225 0.01355 0.00499 -0.1039 0.3637 1.0000
4.500 1.0479 0.01383 0.00525 -0.1035 0.3566 1.0000
4.750 1.0730 0.01413 0.00551 -0.1030 0.3482 1.0000
5.000 1.0980 0.01443 0.00579 -0.1026 0.3399 1.0000
5.250 1.1227 0.01475 0.00610 -0.1021 0.3320 1.0000
5.500 1.1478 0.01504 0.00640 -0.1017 0.3252 1.0000
5.750 1.1726 0.01534 0.00673 -0.1013 0.3189 1.0000
6.000 1.1971 0.01568 0.00707 -0.1008 0.3134 1.0000
6.250 1.2220 0.01596 0.00743 -0.1003 0.3070 1.0000
6.500 1.2458 0.01632 0.00779 -0.0998 0.3006 1.0000
6.750 1.2704 0.01661 0.00817 -0.0993 0.2939 1.0000
7.000 1.2941 0.01696 0.00857 -0.0987 0.2871 1.0000
7.250 1.3179 0.01730 0.00899 -0.0981 0.2818 1.0000
7.500 1.3414 0.01763 0.00940 -0.0975 0.2731 1.0000
7.750 1.3637 0.01800 0.00980 -0.0967 0.2595 1.0000
8.000 1.3854 0.01841 0.01025 -0.0959 0.2438 1.0000
8.250 1.4064 0.01887 0.01073 -0.0950 0.2274 1.0000
8.500 1.4257 0.01945 0.01127 -0.0938 0.2042 1.0000
8.750 1.4394 0.02047 0.01206 -0.0920 0.1619 1.0000
9.000 1.4491 0.02185 0.01319 -0.0897 0.1276 1.0000
9.250 1.4604 0.02304 0.01432 -0.0875 0.1045 1.0000
9.750 1.4657 0.02624 0.01727 -0.0809 0.0472 1.0000
10.000 1.4720 0.02747 0.01859 -0.0781 0.0354 1.0000
10.500 1.4781 0.03057 0.02171 -0.0726 0.0200 1.0000
10.750 1.4805 0.03231 0.02355 -0.0702 0.0182 1.0000
11.000 1.4812 0.03433 0.02571 -0.0681 0.0168 1.0000
11.250 1.4834 0.03635 0.02793 -0.0665 0.0160 1.0000
11.500 1.4834 0.03871 0.03047 -0.0651 0.0151 1.0000
11.750 1.4816 0.04141 0.03333 -0.0640 0.0144 1.0000
12.000 1.4778 0.04450 0.03659 -0.0632 0.0137 1.0000
12.250 1.4717 0.04807 0.04032 -0.0629 0.0132 1.0000
12.500 1.4631 0.05217 0.04458 -0.0629 0.0129 1.0000
12.750 1.4527 0.05672 0.04929 -0.0634 0.0126 1.0000
13.000 1.4402 0.06164 0.05437 -0.0641 0.0124 1.0000
13.250 1.4266 0.06681 0.05970 -0.0649 0.0122 1.0000
13.500 1.4144 0.07188 0.06490 -0.0657 0.0120 1.0000
13.750 1.4051 0.07663 0.06979 -0.0666 0.0119 1.0000
14.000 1.3961 0.08146 0.07476 -0.0676 0.0117 1.0000
14.250 1.3878 0.08625 0.07968 -0.0686 0.0116 1.0000
14.500 1.3801 0.09095 0.08450 -0.0697 0.0114 1.0000
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Polar data table (+)
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