GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Reynolds number: 50,000 Max Cl/Cd: 39.96 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe174-il-50000-n5.txt Download as CSV file: xf-goe174-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.2826 0.10174 0.09549 -0.0264 1.0000 0.0994
-7.250 -0.2918 0.10120 0.09512 -0.0280 1.0000 0.1017
-7.000 -0.2983 0.10078 0.09485 -0.0317 1.0000 0.1026
-6.750 -0.2938 0.09624 0.09041 -0.0286 1.0000 0.1041
-6.500 -0.2894 0.09280 0.08702 -0.0255 1.0000 0.1068
-6.250 -0.2900 0.09063 0.08494 -0.0242 1.0000 0.1099
-6.000 -0.2929 0.08895 0.08336 -0.0243 1.0000 0.1142
-5.750 -0.2937 0.08884 0.08327 -0.0318 1.0000 0.1180
-5.500 -0.2928 0.08461 0.07918 -0.0263 0.9992 0.1207
-5.000 -0.2298 0.07599 0.07046 -0.0385 0.9798 0.1386
-4.500 -0.1501 0.06801 0.06217 -0.0573 0.9563 0.1628
-4.250 -0.1188 0.06419 0.05829 -0.0615 0.9454 0.1777
-4.000 -0.0434 0.05424 0.04756 -0.0782 0.9372 0.0861
-3.750 -0.0083 0.05009 0.04330 -0.0821 0.9271 0.0801
-3.500 0.0365 0.04590 0.03876 -0.0883 0.9171 0.0788
-3.250 0.0885 0.04134 0.03368 -0.0954 0.9099 0.0761
-3.000 0.1382 0.03726 0.02863 -0.1007 0.8998 0.0720
-2.750 0.1823 0.03430 0.02523 -0.1046 0.8917 0.0726
-2.500 0.2193 0.03233 0.02310 -0.1070 0.8805 0.0757
-2.250 0.2580 0.03031 0.02058 -0.1091 0.8684 0.0761
-2.000 0.2966 0.02854 0.01834 -0.1107 0.8561 0.0763
-1.750 0.3338 0.02710 0.01650 -0.1119 0.8430 0.0771
-1.500 0.3685 0.02596 0.01503 -0.1125 0.8289 0.0786
-1.250 0.4009 0.02513 0.01387 -0.1126 0.8141 0.0830
-1.000 0.4330 0.02445 0.01284 -0.1125 0.7993 0.0868
-0.750 0.4633 0.02376 0.01200 -0.1123 0.7847 0.0897
-0.500 0.4923 0.02326 0.01135 -0.1120 0.7699 0.0938
-0.250 0.5204 0.02289 0.01082 -0.1115 0.7550 0.0997
0.000 0.5482 0.02253 0.01042 -0.1110 0.7402 0.1094
0.250 0.5759 0.02214 0.01021 -0.1107 0.7256 0.1433
0.750 0.6269 0.02014 0.00981 -0.1089 0.6970 1.0000
1.000 0.6542 0.02032 0.00965 -0.1083 0.6826 1.0000
1.250 0.6814 0.02053 0.00958 -0.1077 0.6684 1.0000
1.500 0.7084 0.02077 0.00956 -0.1072 0.6543 1.0000
1.750 0.7352 0.02104 0.00961 -0.1066 0.6401 1.0000
2.000 0.7618 0.02134 0.00971 -0.1061 0.6261 1.0000
2.250 0.7883 0.02167 0.00987 -0.1056 0.6123 1.0000
2.500 0.8146 0.02203 0.01009 -0.1051 0.5986 1.0000
2.750 0.8407 0.02241 0.01033 -0.1046 0.5851 1.0000
3.000 0.8668 0.02279 0.01058 -0.1041 0.5722 1.0000
3.250 0.8915 0.02325 0.01100 -0.1035 0.5584 1.0000
3.500 0.9160 0.02371 0.01143 -0.1029 0.5452 1.0000
3.750 0.9406 0.02419 0.01188 -0.1023 0.5327 1.0000
4.000 0.9654 0.02465 0.01233 -0.1018 0.5212 1.0000
4.250 0.9911 0.02507 0.01269 -0.1013 0.5111 1.0000
4.500 1.0146 0.02564 0.01330 -0.1006 0.4995 1.0000
4.750 1.0387 0.02620 0.01391 -0.1001 0.4892 1.0000
5.000 1.0645 0.02664 0.01431 -0.0996 0.4809 1.0000
5.250 1.0872 0.02733 0.01511 -0.0990 0.4709 1.0000
5.500 1.1117 0.02791 0.01572 -0.0984 0.4627 1.0000
5.750 1.1352 0.02855 0.01648 -0.0979 0.4541 1.0000
6.000 1.1587 0.02925 0.01726 -0.0973 0.4464 1.0000
6.250 1.1823 0.02993 0.01804 -0.0967 0.4388 1.0000
6.500 1.2050 0.03071 0.01897 -0.0961 0.4314 1.0000
6.750 1.2279 0.03146 0.01985 -0.0954 0.4240 1.0000
7.000 1.2500 0.03227 0.02080 -0.0947 0.4167 1.0000
7.250 1.2718 0.03304 0.02172 -0.0939 0.4088 1.0000
7.500 1.2920 0.03387 0.02275 -0.0929 0.4002 1.0000
7.750 1.3150 0.03441 0.02338 -0.0921 0.3917 1.0000
8.000 1.3315 0.03542 0.02463 -0.0907 0.3821 1.0000
8.250 1.3550 0.03595 0.02524 -0.0899 0.3742 1.0000
8.500 1.3699 0.03708 0.02670 -0.0884 0.3651 1.0000
8.750 1.3898 0.03788 0.02767 -0.0873 0.3572 1.0000
9.000 1.4063 0.03883 0.02886 -0.0859 0.3483 1.0000
9.250 1.4207 0.03990 0.03018 -0.0843 0.3395 1.0000
9.500 1.4411 0.04048 0.03091 -0.0831 0.3309 1.0000
9.750 1.4483 0.04196 0.03278 -0.0809 0.3217 1.0000
10.000 1.4617 0.04265 0.03366 -0.0789 0.3112 1.0000
10.250 1.4694 0.04319 0.03436 -0.0762 0.2977 1.0000
10.500 1.4688 0.04404 0.03537 -0.0728 0.2831 1.0000
10.750 1.4618 0.04527 0.03677 -0.0689 0.2697 1.0000
11.000 1.4488 0.04751 0.03926 -0.0656 0.2576 1.0000
11.250 1.4366 0.05009 0.04204 -0.0631 0.2451 1.0000
11.500 1.4238 0.05319 0.04534 -0.0616 0.2317 1.0000
11.750 1.4102 0.05693 0.04929 -0.0609 0.2178 1.0000
12.000 1.3955 0.06134 0.05388 -0.0610 0.2038 1.0000
12.250 1.3792 0.06641 0.05912 -0.0617 0.1893 1.0000
12.500 1.3627 0.07179 0.06461 -0.0628 0.1729 1.0000
12.750 1.3477 0.07696 0.06976 -0.0638 0.1530 1.0000
13.000 1.3320 0.08223 0.07488 -0.0648 0.1330 1.0000
13.250 1.3142 0.08810 0.08063 -0.0662 0.1170 1.0000
13.500 1.2964 0.09434 0.08686 -0.0679 0.1025 1.0000
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Polar data table (+)
Polar graphs
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