GOE 371 AIRFOIL (goe371-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: GOE 371 AIRFOIL (goe371-il) Reynolds number: 50,000 Max Cl/Cd: 43.34 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe371-il-50000-n5.txt Download as CSV file: xf-goe371-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 371 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3182 0.10066 0.09408 -0.0282 1.0000 0.0879
-7.500 -0.3250 0.09934 0.09289 -0.0278 1.0000 0.0905
-7.250 -0.3344 0.09870 0.09241 -0.0292 1.0000 0.0923
-7.000 -0.3400 0.09791 0.09175 -0.0324 1.0000 0.0930
-6.750 -0.3356 0.09332 0.08724 -0.0293 1.0000 0.0945
-6.500 -0.3314 0.08990 0.08388 -0.0263 1.0000 0.0975
-6.250 -0.3317 0.08761 0.08166 -0.0255 1.0000 0.1007
-6.000 -0.3333 0.08572 0.07985 -0.0263 1.0000 0.1047
-5.750 -0.3309 0.08496 0.07907 -0.0335 1.0000 0.1077
-5.500 -0.3304 0.08098 0.07520 -0.0298 1.0000 0.1092
-5.250 -0.3288 0.07809 0.07237 -0.0264 1.0000 0.1132
-5.000 -0.3124 0.07674 0.07083 -0.0357 1.0000 0.1225
-4.750 -0.3155 0.07274 0.06701 -0.0292 1.0000 0.1258
-4.500 -0.2962 0.07054 0.06464 -0.0357 1.0000 0.1375
-4.250 -0.2930 0.06695 0.06116 -0.0320 0.9997 0.1407
-3.750 -0.1872 0.05562 0.04884 -0.0535 0.9882 0.0930
-3.500 -0.1441 0.05014 0.04294 -0.0592 0.9820 0.0783
-3.250 -0.1084 0.04600 0.03869 -0.0629 0.9749 0.0744
-3.000 -0.0631 0.04190 0.03413 -0.0683 0.9668 0.0712
-2.750 -0.0203 0.03876 0.03044 -0.0725 0.9579 0.0743
-2.500 0.0241 0.03572 0.02683 -0.0765 0.9507 0.0734
-2.250 0.0613 0.03334 0.02392 -0.0786 0.9424 0.0727
-2.000 0.1014 0.03139 0.02140 -0.0811 0.9358 0.0748
-1.750 0.1372 0.03001 0.01944 -0.0824 0.9274 0.0782
-1.500 0.1744 0.02862 0.01763 -0.0840 0.9203 0.0786
-1.250 0.2095 0.02740 0.01617 -0.0853 0.9123 0.0795
-1.000 0.2433 0.02643 0.01498 -0.0862 0.9040 0.0809
-0.750 0.2827 0.02561 0.01393 -0.0880 0.8967 0.0834
-0.500 0.3171 0.02500 0.01314 -0.0890 0.8876 0.0867
-0.250 0.3584 0.02439 0.01238 -0.0912 0.8807 0.0965
0.000 0.3896 0.02400 0.01190 -0.0917 0.8699 0.1067
0.250 0.4234 0.02352 0.01142 -0.0925 0.8599 0.1194
0.500 0.4633 0.02259 0.01090 -0.0946 0.8523 0.1983
1.000 0.5275 0.02087 0.01047 -0.0955 0.8293 1.0000
1.250 0.5586 0.02096 0.01036 -0.0957 0.8174 1.0000
1.500 0.5903 0.02103 0.01027 -0.0960 0.8056 1.0000
1.750 0.6232 0.02105 0.01017 -0.0963 0.7943 1.0000
2.000 0.6520 0.02117 0.01021 -0.0961 0.7809 1.0000
2.250 0.6802 0.02132 0.01029 -0.0958 0.7670 1.0000
2.500 0.7082 0.02147 0.01041 -0.0954 0.7529 1.0000
2.750 0.7358 0.02165 0.01056 -0.0950 0.7388 1.0000
3.000 0.7631 0.02185 0.01074 -0.0945 0.7245 1.0000
3.250 0.7898 0.02208 0.01098 -0.0939 0.7100 1.0000
3.500 0.8161 0.02231 0.01125 -0.0933 0.6952 1.0000
3.750 0.8425 0.02243 0.01138 -0.0924 0.6786 1.0000
4.000 0.8659 0.02254 0.01150 -0.0910 0.6578 1.0000
4.250 0.8897 0.02257 0.01157 -0.0895 0.6361 1.0000
4.500 0.9133 0.02267 0.01169 -0.0882 0.6151 1.0000
4.750 0.9372 0.02287 0.01193 -0.0870 0.5960 1.0000
5.000 0.9624 0.02306 0.01219 -0.0860 0.5785 1.0000
5.250 0.9879 0.02328 0.01244 -0.0851 0.5614 1.0000
5.500 1.0115 0.02363 0.01285 -0.0840 0.5427 1.0000
5.750 1.0353 0.02402 0.01331 -0.0829 0.5237 1.0000
6.000 1.0593 0.02444 0.01382 -0.0818 0.5045 1.0000
6.250 1.0816 0.02497 0.01444 -0.0806 0.4837 1.0000
6.500 1.1031 0.02555 0.01513 -0.0793 0.4619 1.0000
6.750 1.1236 0.02617 0.01586 -0.0779 0.4389 1.0000
7.000 1.1431 0.02682 0.01667 -0.0763 0.4146 1.0000
7.250 1.1606 0.02755 0.01755 -0.0745 0.3884 1.0000
7.500 1.1767 0.02829 0.01840 -0.0725 0.3605 1.0000
7.750 1.1915 0.02907 0.01926 -0.0705 0.3322 1.0000
8.000 1.2053 0.02992 0.02014 -0.0683 0.3049 1.0000
8.250 1.2186 0.03088 0.02109 -0.0662 0.2808 1.0000
8.500 1.2321 0.03199 0.02233 -0.0642 0.2590 1.0000
8.750 1.2420 0.03325 0.02357 -0.0620 0.2358 1.0000
9.000 1.2461 0.03469 0.02493 -0.0593 0.2090 1.0000
9.250 1.2470 0.03627 0.02647 -0.0563 0.1829 1.0000
9.500 1.2483 0.03791 0.02821 -0.0536 0.1579 1.0000
9.750 1.2469 0.03982 0.03015 -0.0511 0.1291 1.0000
10.000 1.2444 0.04212 0.03241 -0.0489 0.1013 1.0000
10.250 1.2394 0.04496 0.03514 -0.0469 0.0809 1.0000
10.500 1.2328 0.04822 0.03833 -0.0451 0.0682 1.0000
10.750 1.2251 0.05173 0.04175 -0.0438 0.0608 1.0000
11.000 1.2225 0.05499 0.04522 -0.0427 0.0537 1.0000
11.250 1.2167 0.05861 0.04889 -0.0421 0.0494 1.0000
11.500 1.2143 0.06210 0.05262 -0.0414 0.0456 1.0000
11.750 1.2131 0.06558 0.05632 -0.0409 0.0426 1.0000
12.000 1.2117 0.06914 0.06003 -0.0406 0.0406 1.0000
12.250 1.2094 0.07285 0.06384 -0.0405 0.0390 1.0000
12.500 1.2088 0.07664 0.06783 -0.0403 0.0373 1.0000
12.750 1.2071 0.08079 0.07231 -0.0406 0.0357 1.0000
13.000 1.2031 0.08529 0.07708 -0.0414 0.0345 1.0000
13.250 1.1967 0.09022 0.08224 -0.0428 0.0334 1.0000
13.500 1.1894 0.09544 0.08767 -0.0445 0.0326 1.0000
13.750 1.1808 0.10102 0.09345 -0.0467 0.0319 1.0000
14.000 1.1712 0.10709 0.09972 -0.0493 0.0316 1.0000
14.250 1.1600 0.11375 0.10660 -0.0525 0.0314 1.0000
14.500 1.1456 0.12161 0.11469 -0.0568 0.0315 1.0000
14.750 1.1239 0.13218 0.12554 -0.0631 0.0323 1.0000
15.000 1.0966 0.14568 0.13922 -0.0712 0.0341 1.0000
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Polar data table (+)
Polar graphs
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