GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Reynolds number: 500,000 Max Cl/Cd: 101.92 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe174-il-500000-n5.txt Download as CSV file: xf-goe174-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2972 0.10364 0.10140 -0.0266 1.0000 0.0082
-9.000 -0.2958 0.10026 0.09803 -0.0272 1.0000 0.0083
-8.750 -0.2959 0.09677 0.09458 -0.0278 1.0000 0.0084
-8.250 -0.2790 0.09123 0.08909 -0.0311 0.9964 0.0087
-7.750 -0.2487 0.08502 0.08289 -0.0379 0.9758 0.0095
-7.500 -0.2308 0.08070 0.07856 -0.0434 0.9478 0.0099
-7.250 -0.1998 0.07479 0.07259 -0.0536 0.9241 0.0102
-7.000 -0.1753 0.06915 0.06682 -0.0622 0.8968 0.0105
-6.750 -0.1555 0.06152 0.05905 -0.0725 0.8744 0.0111
-6.500 -0.1343 0.05887 0.05630 -0.0761 0.8568 0.0114
-6.250 -0.1126 0.05675 0.05407 -0.0790 0.8397 0.0118
-6.000 -0.0887 0.05345 0.05067 -0.0834 0.8230 0.0126
-5.750 -0.0597 0.04766 0.04470 -0.0908 0.8073 0.0134
-5.500 -0.0239 0.03889 0.03564 -0.1008 0.7927 0.0146
-5.000 0.0410 0.02265 0.01827 -0.1117 0.7571 0.0184
-4.750 0.0658 0.02221 0.01763 -0.1116 0.7220 0.0188
-4.500 0.0904 0.02189 0.01707 -0.1113 0.6833 0.0193
-4.250 0.1167 0.02038 0.01520 -0.1116 0.6611 0.0204
-4.000 0.1446 0.01788 0.01212 -0.1120 0.6465 0.0218
-3.750 0.1725 0.01666 0.01039 -0.1120 0.6339 0.0231
-3.500 0.1993 0.01564 0.00921 -0.1122 0.6230 0.0237
-3.250 0.2266 0.01498 0.00840 -0.1122 0.6140 0.0242
-3.000 0.2541 0.01438 0.00763 -0.1121 0.6060 0.0247
-2.750 0.2819 0.01383 0.00693 -0.1121 0.5984 0.0253
-2.500 0.3096 0.01341 0.00636 -0.1120 0.5901 0.0263
-2.250 0.3375 0.01291 0.00571 -0.1120 0.5825 0.0268
-2.000 0.3653 0.01248 0.00515 -0.1119 0.5749 0.0273
-1.750 0.3933 0.01212 0.00468 -0.1118 0.5680 0.0277
-1.500 0.4211 0.01181 0.00429 -0.1117 0.5599 0.0280
-1.250 0.4488 0.01154 0.00394 -0.1116 0.5516 0.0283
-1.000 0.4764 0.01137 0.00369 -0.1114 0.5418 0.0286
-0.750 0.5041 0.01119 0.00345 -0.1113 0.5301 0.0291
-0.500 0.5315 0.01086 0.00307 -0.1112 0.5174 0.0294
-0.250 0.5588 0.01064 0.00279 -0.1110 0.5024 0.0297
0.000 0.5861 0.01050 0.00257 -0.1109 0.4863 0.0302
0.250 0.6132 0.01041 0.00241 -0.1107 0.4700 0.0308
0.500 0.6403 0.01039 0.00231 -0.1106 0.4528 0.0315
0.750 0.6673 0.01041 0.00225 -0.1104 0.4363 0.0322
1.250 0.7212 0.01054 0.00222 -0.1100 0.4055 0.0338
1.500 0.7481 0.01063 0.00224 -0.1098 0.3914 0.0349
1.750 0.7749 0.01074 0.00228 -0.1096 0.3782 0.0363
2.250 0.8284 0.01099 0.00240 -0.1092 0.3543 0.0393
2.500 0.8551 0.01112 0.00250 -0.1089 0.3444 0.0456
2.750 0.8822 0.01099 0.00269 -0.1090 0.3371 0.2046
3.750 0.9849 0.01019 0.00337 -0.1077 0.3067 1.0000
4.000 1.0112 0.01040 0.00353 -0.1075 0.3005 1.0000
4.250 1.0378 0.01057 0.00368 -0.1073 0.2944 1.0000
4.500 1.0640 0.01077 0.00386 -0.1070 0.2876 1.0000
4.750 1.0902 0.01097 0.00404 -0.1068 0.2819 1.0000
5.000 1.1165 0.01116 0.00422 -0.1066 0.2755 1.0000
5.250 1.1423 0.01139 0.00443 -0.1063 0.2696 1.0000
5.500 1.1685 0.01156 0.00463 -0.1060 0.2644 1.0000
5.750 1.1943 0.01178 0.00484 -0.1057 0.2576 1.0000
6.000 1.2198 0.01201 0.00508 -0.1054 0.2518 1.0000
6.250 1.2455 0.01222 0.00531 -0.1051 0.2452 1.0000
6.500 1.2700 0.01255 0.00558 -0.1047 0.2305 1.0000
6.750 1.2928 0.01302 0.00592 -0.1040 0.2048 1.0000
7.000 1.3113 0.01393 0.00653 -0.1028 0.1550 1.0000
7.250 1.3303 0.01477 0.00718 -0.1016 0.1252 1.0000
7.500 1.3517 0.01533 0.00770 -0.1007 0.1128 1.0000
7.750 1.3734 0.01585 0.00820 -0.0998 0.1017 1.0000
8.000 1.3917 0.01668 0.00888 -0.0985 0.0660 1.0000
8.250 1.4087 0.01758 0.00970 -0.0970 0.0506 1.0000
8.500 1.4288 0.01815 0.01031 -0.0959 0.0439 1.0000
8.750 1.4480 0.01878 0.01095 -0.0947 0.0344 1.0000
9.000 1.4621 0.01979 0.01185 -0.0929 0.0165 1.0000
9.250 1.4788 0.02054 0.01265 -0.0913 0.0137 1.0000
9.500 1.4946 0.02130 0.01348 -0.0896 0.0118 1.0000
9.750 1.5104 0.02198 0.01424 -0.0879 0.0109 1.0000
10.000 1.5227 0.02273 0.01508 -0.0856 0.0101 1.0000
10.250 1.5327 0.02362 0.01604 -0.0831 0.0094 1.0000
10.500 1.5399 0.02472 0.01725 -0.0803 0.0088 1.0000
10.750 1.5479 0.02580 0.01843 -0.0779 0.0084 1.0000
11.000 1.5565 0.02690 0.01963 -0.0757 0.0080 1.0000
11.250 1.5638 0.02815 0.02097 -0.0736 0.0075 1.0000
11.500 1.5697 0.02960 0.02252 -0.0717 0.0071 1.0000
11.750 1.5746 0.03122 0.02424 -0.0700 0.0068 1.0000
12.000 1.5775 0.03317 0.02629 -0.0685 0.0066 1.0000
12.250 1.5776 0.03550 0.02874 -0.0671 0.0063 1.0000
12.500 1.5740 0.03839 0.03176 -0.0660 0.0061 1.0000
12.750 1.5690 0.04163 0.03512 -0.0652 0.0060 1.0000
13.000 1.5672 0.04472 0.03835 -0.0649 0.0059 1.0000
13.250 1.5635 0.04822 0.04198 -0.0649 0.0058 1.0000
13.500 1.5581 0.05207 0.04596 -0.0651 0.0057 1.0000
13.750 1.5511 0.05622 0.05025 -0.0655 0.0055 1.0000
14.000 1.5423 0.06064 0.05481 -0.0661 0.0055 1.0000
14.250 1.5321 0.06532 0.05961 -0.0667 0.0054 1.0000
14.500 1.5215 0.07020 0.06462 -0.0675 0.0053 1.0000
14.750 1.5102 0.07527 0.06982 -0.0685 0.0052 1.0000
15.000 1.4989 0.08046 0.07513 -0.0697 0.0052 1.0000
15.250 1.4879 0.08573 0.08052 -0.0709 0.0051 1.0000
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Polar data table (+)
Polar graphs
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