GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Reynolds number: 100,000 Max Cl/Cd: 53.23 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe174-il-100000.txt Download as CSV file: xf-goe174-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2897 0.09638 0.09184 -0.0259 1.0000 0.0674
-7.250 -0.2978 0.09566 0.09126 -0.0278 1.0000 0.0689
-7.000 -0.3018 0.09525 0.09095 -0.0334 1.0000 0.0696
-6.750 -0.3018 0.09378 0.08956 -0.0374 1.0000 0.0700
-6.500 -0.3021 0.08775 0.08362 -0.0279 1.0000 0.0716
-6.250 -0.3024 0.08525 0.08119 -0.0242 1.0000 0.0734
-6.000 -0.3054 0.08342 0.07943 -0.0223 1.0000 0.0756
-5.750 -0.3084 0.08171 0.07778 -0.0217 1.0000 0.0784
-5.500 -0.3072 0.08027 0.07637 -0.0248 1.0000 0.0823
-5.250 -0.2925 0.07770 0.07375 -0.0341 0.9991 0.0850
-5.000 -0.2739 0.07306 0.06918 -0.0318 0.9938 0.0887
-4.750 -0.2065 0.06762 0.06347 -0.0507 0.9843 0.1004
-4.500 -0.1831 0.06355 0.05947 -0.0504 0.9759 0.1050
-4.250 -0.1318 0.05887 0.05460 -0.0612 0.9661 0.1175
-4.000 -0.0842 0.05477 0.05039 -0.0690 0.9586 0.1328
-3.750 -0.0395 0.05102 0.04651 -0.0756 0.9480 0.1475
-3.500 0.0045 0.04750 0.04287 -0.0813 0.9375 0.1633
-3.000 0.1105 0.04096 0.03588 -0.0954 0.9201 0.2190
-2.750 0.1485 0.03750 0.03243 -0.0980 0.9097 0.2378
-2.250 0.2793 0.01146 0.00491 -0.1092 0.8613 0.1309
-2.000 0.3182 0.02461 0.01718 -0.1149 0.8801 0.1104
-1.750 0.3594 0.02267 0.01449 -0.1160 0.8681 0.0991
-1.500 0.3941 0.02102 0.01258 -0.1166 0.8550 0.0970
-1.250 0.4259 0.02000 0.01130 -0.1165 0.8407 0.0973
-1.000 0.4555 0.01936 0.01040 -0.1160 0.8257 0.0993
-0.750 0.4833 0.01854 0.00949 -0.1153 0.8106 0.1002
-0.500 0.5101 0.01788 0.00880 -0.1145 0.7955 0.1023
-0.250 0.5366 0.01741 0.00831 -0.1136 0.7804 0.1061
0.000 0.5627 0.01708 0.00789 -0.1125 0.7653 0.1123
0.250 0.5893 0.01675 0.00754 -0.1117 0.7501 0.1267
0.500 0.6167 0.01618 0.00739 -0.1111 0.7349 0.2501
0.750 0.6432 0.01454 0.00711 -0.1099 0.7198 1.0000
1.000 0.6698 0.01469 0.00696 -0.1091 0.7040 1.0000
1.250 0.6958 0.01487 0.00691 -0.1083 0.6873 1.0000
1.500 0.7218 0.01509 0.00690 -0.1075 0.6703 1.0000
1.750 0.7479 0.01535 0.00696 -0.1068 0.6533 1.0000
2.000 0.7739 0.01567 0.00709 -0.1061 0.6365 1.0000
2.250 0.7997 0.01603 0.00727 -0.1054 0.6196 1.0000
2.500 0.8255 0.01641 0.00749 -0.1048 0.6030 1.0000
2.750 0.8511 0.01681 0.00775 -0.1041 0.5868 1.0000
3.000 0.8767 0.01721 0.00805 -0.1035 0.5715 1.0000
3.250 0.9022 0.01762 0.00838 -0.1030 0.5572 1.0000
3.500 0.9277 0.01803 0.00871 -0.1025 0.5438 1.0000
3.750 0.9534 0.01842 0.00905 -0.1020 0.5315 1.0000
4.000 0.9799 0.01879 0.00930 -0.1015 0.5209 1.0000
4.250 1.0049 0.01921 0.00975 -0.1010 0.5095 1.0000
4.500 1.0301 0.01967 0.01021 -0.1006 0.4991 1.0000
4.750 1.0565 0.02005 0.01054 -0.1002 0.4901 1.0000
5.000 1.0813 0.02047 0.01100 -0.0997 0.4798 1.0000
5.250 1.1062 0.02094 0.01150 -0.0992 0.4703 1.0000
5.500 1.1327 0.02133 0.01182 -0.0988 0.4623 1.0000
5.750 1.1564 0.02185 0.01250 -0.0982 0.4526 1.0000
6.000 1.1823 0.02230 0.01292 -0.0978 0.4447 1.0000
6.250 1.2062 0.02284 0.01357 -0.0973 0.4360 1.0000
6.500 1.2310 0.02337 0.01417 -0.0968 0.4279 1.0000
6.750 1.2557 0.02379 0.01463 -0.0962 0.4190 1.0000
7.000 1.2785 0.02436 0.01533 -0.0954 0.4096 1.0000
7.250 1.3043 0.02475 0.01567 -0.0950 0.4009 1.0000
7.500 1.3259 0.02528 0.01641 -0.0941 0.3910 1.0000
7.750 1.3492 0.02587 0.01711 -0.0934 0.3825 1.0000
8.000 1.3733 0.02639 0.01771 -0.0928 0.3743 1.0000
8.250 1.3946 0.02711 0.01864 -0.0918 0.3658 1.0000
8.500 1.4187 0.02746 0.01901 -0.0912 0.3556 1.0000
8.750 1.4401 0.02760 0.01916 -0.0900 0.3420 1.0000
9.000 1.4579 0.02769 0.01935 -0.0883 0.3268 1.0000
9.250 1.4732 0.02780 0.01960 -0.0862 0.3110 1.0000
9.500 1.4870 0.02795 0.01997 -0.0840 0.2951 1.0000
9.750 1.4995 0.02817 0.02043 -0.0816 0.2787 1.0000
10.000 1.5079 0.02834 0.02083 -0.0786 0.2564 1.0000
10.250 1.5086 0.02883 0.02140 -0.0746 0.2110 1.0000
10.500 1.4905 0.03122 0.02320 -0.0689 0.1354 1.0000
10.750 1.4710 0.03443 0.02608 -0.0639 0.0969 1.0000
11.000 1.4560 0.03765 0.02914 -0.0604 0.0762 1.0000
11.250 1.4415 0.04115 0.03259 -0.0579 0.0694 1.0000
11.500 1.4280 0.04493 0.03649 -0.0564 0.0653 1.0000
11.750 1.4127 0.04924 0.04090 -0.0556 0.0625 1.0000
12.000 1.3962 0.05405 0.04580 -0.0555 0.0605 1.0000
12.250 1.3838 0.05860 0.05048 -0.0555 0.0585 1.0000
12.500 1.3747 0.06283 0.05486 -0.0555 0.0564 1.0000
12.750 1.3675 0.06668 0.05881 -0.0552 0.0545 1.0000
13.000 1.3646 0.06975 0.06193 -0.0542 0.0524 1.0000
13.250 1.3875 0.06872 0.06054 -0.0480 0.0487 1.0000
13.500 1.3935 0.07119 0.06322 -0.0471 0.0473 1.0000
13.750 1.3991 0.07378 0.06600 -0.0461 0.0455 1.0000
14.000 1.4067 0.07623 0.06859 -0.0449 0.0436 1.0000
14.250 1.4172 0.07859 0.07108 -0.0434 0.0423 1.0000
14.500 1.4264 0.08133 0.07400 -0.0421 0.0415 1.0000
14.750 1.4315 0.08466 0.07752 -0.0413 0.0409 1.0000
15.000 1.4311 0.08861 0.08169 -0.0411 0.0406 1.0000
15.250 1.4249 0.09314 0.08647 -0.0416 0.0406 1.0000
15.500 1.4142 0.09815 0.09174 -0.0428 0.0406 1.0000
15.750 1.4002 0.10366 0.09751 -0.0446 0.0407 1.0000
16.000 1.3835 0.10974 0.10386 -0.0472 0.0409 1.0000
16.250 1.3614 0.11695 0.11135 -0.0512 0.0413 1.0000
16.500 1.3324 0.12597 0.12069 -0.0571 0.0420 1.0000
16.750 1.3027 0.13612 0.13113 -0.0642 0.0428 1.0000
17.000 1.2714 0.14773 0.14298 -0.0725 0.0438 1.0000
17.250 1.2362 0.16161 0.15704 -0.0826 0.0450 1.0000
17.500 1.2015 0.17712 0.17264 -0.0933 0.0467 1.0000
17.750 1.1839 0.18870 0.18420 -0.1002 0.0481 1.0000
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