GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Reynolds number: 1,000,000 Max Cl/Cd: 125.85 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe174-il-1000000.txt Download as CSV file: xf-goe174-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2281 0.09893 0.09744 -0.0284 1.0000 0.0121
-9.500 -0.2246 0.09624 0.09476 -0.0284 1.0000 0.0123
-9.250 -0.3136 0.10322 0.10162 -0.0249 1.0000 0.0120
-9.000 -0.3080 0.10075 0.09916 -0.0249 1.0000 0.0121
-8.750 -0.3031 0.09837 0.09680 -0.0250 1.0000 0.0122
-8.500 -0.2993 0.09601 0.09445 -0.0251 1.0000 0.0124
-8.250 -0.2966 0.09367 0.09214 -0.0250 1.0000 0.0126
-8.000 -0.2957 0.09141 0.08991 -0.0247 1.0000 0.0128
-7.750 -0.2902 0.08869 0.08721 -0.0258 0.9992 0.0132
-7.500 -0.1577 0.06239 0.06092 -0.0528 0.9455 0.0150
-6.000 -0.1110 0.05657 0.05454 -0.0760 0.8514 0.0166
-5.250 -0.0159 0.03747 0.03488 -0.0986 0.8089 0.0192
-5.000 0.0073 0.03610 0.03342 -0.0995 0.7929 0.0195
-4.750 0.0328 0.03414 0.03133 -0.1010 0.7750 0.0201
-4.500 0.0718 0.02761 0.02430 -0.1049 0.7574 0.0232
-4.250 0.0970 0.02055 0.01655 -0.1074 0.7356 0.0239
-4.000 0.1214 0.01968 0.01554 -0.1074 0.7001 0.0243
-3.750 0.1466 0.01892 0.01458 -0.1074 0.6695 0.0250
-3.500 0.1731 0.01802 0.01346 -0.1074 0.6499 0.0262
-3.250 0.2026 0.01861 0.01373 -0.1069 0.6364 0.0289
-3.000 0.2295 0.01505 0.00965 -0.1074 0.6270 0.0298
-2.750 0.2565 0.01400 0.00854 -0.1075 0.6176 0.0307
-2.500 0.2841 0.01337 0.00782 -0.1076 0.6093 0.0317
-2.250 0.3119 0.01286 0.00718 -0.1075 0.6008 0.0333
-2.000 0.3405 0.01374 0.00799 -0.1072 0.5933 0.0362
-1.750 0.3679 0.01161 0.00565 -0.1075 0.5864 0.0392
-1.500 0.3959 0.01120 0.00519 -0.1075 0.5795 0.0413
-1.250 0.4249 0.01046 0.00427 -0.1071 0.5718 0.0346
-1.000 0.4530 0.00972 0.00340 -0.1069 0.5642 0.0320
-0.750 0.4810 0.00941 0.00304 -0.1068 0.5552 0.0323
-0.500 0.5090 0.00909 0.00267 -0.1067 0.5447 0.0321
-0.250 0.5368 0.00888 0.00240 -0.1066 0.5325 0.0324
0.000 0.5646 0.00874 0.00220 -0.1064 0.5190 0.0329
0.250 0.5923 0.00864 0.00204 -0.1063 0.5053 0.0333
0.500 0.6200 0.00857 0.00191 -0.1062 0.4904 0.0337
0.750 0.6476 0.00855 0.00181 -0.1061 0.4736 0.0340
1.000 0.6751 0.00856 0.00175 -0.1060 0.4559 0.0348
1.250 0.7024 0.00861 0.00171 -0.1058 0.4374 0.0355
1.500 0.7295 0.00869 0.00170 -0.1056 0.4190 0.0360
1.750 0.7566 0.00878 0.00169 -0.1054 0.4016 0.0375
2.000 0.7837 0.00888 0.00171 -0.1052 0.3860 0.0403
2.250 0.8108 0.00899 0.00177 -0.1051 0.3719 0.0449
2.500 0.8380 0.00886 0.00193 -0.1051 0.3595 0.2117
2.750 0.8613 0.00747 0.00221 -0.1046 0.3473 1.0000
3.000 0.8883 0.00765 0.00230 -0.1045 0.3364 1.0000
3.250 0.9153 0.00783 0.00241 -0.1043 0.3281 1.0000
3.500 0.9426 0.00795 0.00251 -0.1042 0.3222 1.0000
3.750 0.9696 0.00812 0.00263 -0.1040 0.3149 1.0000
4.000 0.9967 0.00827 0.00274 -0.1039 0.3086 1.0000
4.250 1.0237 0.00841 0.00286 -0.1037 0.3026 1.0000
4.500 1.0504 0.00859 0.00301 -0.1036 0.2966 1.0000
4.750 1.0776 0.00872 0.00313 -0.1035 0.2916 1.0000
5.000 1.1042 0.00889 0.00328 -0.1033 0.2854 1.0000
5.250 1.1310 0.00905 0.00343 -0.1031 0.2804 1.0000
5.500 1.1578 0.00920 0.00358 -0.1030 0.2739 1.0000
5.750 1.1840 0.00941 0.00375 -0.1027 0.2639 1.0000
6.000 1.2098 0.00964 0.00393 -0.1025 0.2529 1.0000
6.250 1.2358 0.00985 0.00412 -0.1022 0.2420 1.0000
6.500 1.2609 0.01016 0.00434 -0.1019 0.2256 1.0000
6.750 1.2856 0.01050 0.00460 -0.1014 0.2076 1.0000
7.000 1.3075 0.01111 0.00501 -0.1006 0.1721 1.0000
7.250 1.3262 0.01205 0.00567 -0.0993 0.1279 1.0000
7.500 1.3489 0.01256 0.00611 -0.0986 0.1133 1.0000
7.750 1.3721 0.01300 0.00650 -0.0980 0.1024 1.0000
8.000 1.3893 0.01403 0.00726 -0.0965 0.0579 1.0000
8.250 1.4110 0.01457 0.00780 -0.0956 0.0484 1.0000
8.500 1.4322 0.01515 0.00838 -0.0947 0.0393 1.0000
8.750 1.4501 0.01602 0.00909 -0.0932 0.0197 1.0000
9.000 1.4702 0.01663 0.00972 -0.0921 0.0159 1.0000
9.250 1.4891 0.01734 0.01047 -0.0908 0.0138 1.0000
9.500 1.5093 0.01787 0.01106 -0.0897 0.0131 1.0000
9.750 1.5284 0.01847 0.01172 -0.0884 0.0123 1.0000
10.000 1.5459 0.01915 0.01245 -0.0870 0.0114 1.0000
10.250 1.5595 0.02009 0.01347 -0.0849 0.0106 1.0000
10.500 1.5715 0.02104 0.01452 -0.0827 0.0101 1.0000
10.750 1.5848 0.02171 0.01526 -0.0805 0.0098 1.0000
11.000 1.5952 0.02250 0.01612 -0.0780 0.0095 1.0000
11.250 1.6042 0.02340 0.01710 -0.0754 0.0092 1.0000
11.500 1.6119 0.02443 0.01820 -0.0728 0.0088 1.0000
11.750 1.6183 0.02560 0.01945 -0.0704 0.0086 1.0000
12.000 1.6230 0.02698 0.02092 -0.0680 0.0083 1.0000
12.250 1.6249 0.02872 0.02275 -0.0658 0.0081 1.0000
12.500 1.6213 0.03112 0.02526 -0.0637 0.0078 1.0000
12.750 1.6100 0.03452 0.02881 -0.0619 0.0076 1.0000
13.000 1.6009 0.03804 0.03247 -0.0607 0.0074 1.0000
13.250 1.6055 0.04029 0.03481 -0.0603 0.0073 1.0000
13.500 1.6066 0.04305 0.03767 -0.0601 0.0072 1.0000
13.750 1.6053 0.04626 0.04098 -0.0601 0.0071 1.0000
14.000 1.6016 0.04990 0.04474 -0.0604 0.0070 1.0000
14.250 1.5956 0.05389 0.04884 -0.0609 0.0069 1.0000
14.500 1.5877 0.05815 0.05322 -0.0614 0.0068 1.0000
14.750 1.5785 0.06264 0.05782 -0.0620 0.0067 1.0000
15.000 1.5684 0.06731 0.06259 -0.0627 0.0066 1.0000
15.250 1.5583 0.07214 0.06753 -0.0636 0.0065 1.0000
15.500 1.5481 0.07705 0.07255 -0.0647 0.0064 1.0000
15.750 1.5376 0.08210 0.07769 -0.0658 0.0064 1.0000
16.000 1.5270 0.08724 0.08294 -0.0670 0.0063 1.0000
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Polar data table (+)
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