GOE 380 AIRFOIL (goe380-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 380 AIRFOIL (goe380-il) Reynolds number: 500,000 Max Cl/Cd: 103.44 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe380-il-500000.txt Download as CSV file: xf-goe380-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 380 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3037 0.09080 0.08878 -0.0211 1.0000 0.0101
-7.250 -0.3118 0.08922 0.08726 -0.0185 1.0000 0.0102
-7.000 -0.3206 0.08772 0.08581 -0.0160 1.0000 0.0103
-6.750 -0.3004 0.08380 0.08189 -0.0210 0.9974 0.0105
-6.500 -0.2742 0.07957 0.07763 -0.0275 0.9937 0.0108
-6.250 -0.2479 0.07543 0.07348 -0.0339 0.9890 0.0111
-6.000 -0.2174 0.07109 0.06911 -0.0411 0.9850 0.0114
-5.750 -0.1862 0.06684 0.06483 -0.0480 0.9800 0.0120
-5.500 -0.1537 0.06265 0.06059 -0.0547 0.9742 0.0123
-5.250 -0.1150 0.05818 0.05606 -0.0625 0.9705 0.0133
-5.000 -0.0736 0.05430 0.05209 -0.0699 0.9633 0.0142
-4.750 -0.0314 0.05053 0.04820 -0.0764 0.9571 0.0145
-4.500 0.0004 0.04703 0.04459 -0.0800 0.9467 0.0146
-4.250 0.0288 0.04145 0.03885 -0.0839 0.9345 0.0150
-4.000 0.0513 0.03849 0.03581 -0.0852 0.9201 0.0158
-3.750 0.0759 0.03619 0.03340 -0.0862 0.9040 0.0168
-3.500 0.1022 0.03374 0.03078 -0.0870 0.8876 0.0183
-3.250 0.1373 0.03203 0.02881 -0.0872 0.8707 0.0217
-3.000 0.1592 0.02755 0.02401 -0.0871 0.8535 0.0227
-2.750 0.1789 0.02639 0.02277 -0.0869 0.8353 0.0248
-2.500 0.2033 0.02478 0.02094 -0.0863 0.8180 0.0271
-2.250 0.2344 0.02404 0.01988 -0.0851 0.8003 0.0313
-1.500 0.3032 0.01312 0.00758 -0.0805 0.7459 0.0196
-1.250 0.3281 0.01118 0.00516 -0.0792 0.7243 0.0196
-1.000 0.3529 0.01037 0.00406 -0.0781 0.7004 0.0207
-0.750 0.3773 0.00983 0.00327 -0.0771 0.6756 0.0228
-0.500 0.4010 0.00928 0.00254 -0.0760 0.6513 0.0251
-0.250 0.4255 0.00910 0.00222 -0.0751 0.6293 0.0290
0.000 0.4502 0.00894 0.00196 -0.0742 0.6098 0.0393
0.250 0.4764 0.00912 0.00209 -0.0737 0.5932 0.0686
0.500 0.5026 0.00927 0.00217 -0.0733 0.5790 0.0783
0.750 0.5287 0.00938 0.00220 -0.0729 0.5663 0.0864
1.000 0.5552 0.00955 0.00229 -0.0726 0.5544 0.0946
1.250 0.5802 0.00944 0.00216 -0.0720 0.5425 0.1016
1.500 0.6058 0.00947 0.00211 -0.0715 0.5300 0.1071
1.750 0.6308 0.00940 0.00201 -0.0709 0.5174 0.1147
2.000 0.6562 0.00942 0.00197 -0.0704 0.5053 0.1222
2.250 0.6817 0.00941 0.00196 -0.0699 0.4928 0.1317
2.500 0.7072 0.00941 0.00199 -0.0695 0.4799 0.1513
2.750 0.7806 0.00793 0.00222 -0.0803 0.4592 1.0000
3.000 0.8048 0.00807 0.00227 -0.0796 0.4440 1.0000
3.250 0.8290 0.00823 0.00235 -0.0788 0.4287 1.0000
3.500 0.8529 0.00840 0.00246 -0.0780 0.4134 1.0000
3.750 0.8767 0.00859 0.00257 -0.0772 0.3987 1.0000
4.000 0.9003 0.00879 0.00270 -0.0764 0.3850 1.0000
4.250 0.9239 0.00900 0.00285 -0.0756 0.3725 1.0000
4.500 0.9475 0.00922 0.00301 -0.0748 0.3621 1.0000
4.750 0.9709 0.00945 0.00322 -0.0740 0.3527 1.0000
5.000 0.9949 0.00964 0.00341 -0.0733 0.3440 1.0000
5.250 1.0182 0.00988 0.00362 -0.0725 0.3355 1.0000
5.500 1.0418 0.01009 0.00383 -0.0717 0.3269 1.0000
5.750 1.0654 0.01030 0.00408 -0.0710 0.3189 1.0000
6.000 1.0883 0.01055 0.00431 -0.0701 0.3070 1.0000
6.250 1.1114 0.01079 0.00453 -0.0693 0.2924 1.0000
6.500 1.1344 0.01103 0.00475 -0.0685 0.2762 1.0000
6.750 1.1571 0.01130 0.00500 -0.0677 0.2590 1.0000
7.000 1.1789 0.01165 0.00530 -0.0667 0.2354 1.0000
7.250 1.1973 0.01229 0.00570 -0.0653 0.1915 1.0000
7.500 1.2128 0.01322 0.00635 -0.0635 0.1476 1.0000
7.750 1.2118 0.01567 0.00798 -0.0592 0.0263 1.0000
8.000 1.2290 0.01645 0.00886 -0.0574 0.0184 1.0000
8.250 1.2461 0.01721 0.00972 -0.0557 0.0153 1.0000
8.500 1.2582 0.01839 0.01110 -0.0531 0.0133 1.0000
8.750 1.2717 0.01933 0.01218 -0.0508 0.0126 1.0000
9.000 1.2846 0.02024 0.01321 -0.0485 0.0120 1.0000
9.250 1.2943 0.02131 0.01439 -0.0457 0.0113 1.0000
9.500 1.2995 0.02242 0.01562 -0.0422 0.0107 1.0000
9.750 1.3046 0.02345 0.01673 -0.0388 0.0102 1.0000
10.000 1.3089 0.02456 0.01793 -0.0356 0.0096 1.0000
10.250 1.3089 0.02604 0.01949 -0.0322 0.0091 1.0000
10.500 1.3072 0.02775 0.02130 -0.0290 0.0088 1.0000
10.750 1.3030 0.02986 0.02353 -0.0259 0.0085 1.0000
11.000 1.2918 0.03299 0.02677 -0.0226 0.0081 1.0000
11.250 1.2927 0.03547 0.02933 -0.0205 0.0081 1.0000
11.500 1.2986 0.03831 0.03226 -0.0185 0.0079 1.0000
11.750 1.3020 0.03991 0.03401 -0.0173 0.0077 1.0000
12.000 1.3104 0.04247 0.03668 -0.0158 0.0078 1.0000
12.250 1.3137 0.04478 0.03916 -0.0146 0.0076 1.0000
12.500 1.3378 0.04804 0.04249 -0.0133 0.0082 1.0000
12.750 1.3370 0.04981 0.04440 -0.0122 0.0084 1.0000
17.250 0.8587 0.17362 0.17179 -0.0693 0.0203 1.0000
17.500 0.8474 0.18198 0.18017 -0.0738 0.0202 1.0000
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Polar data table (+)
Polar graphs
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