GOE 374 AIRFOIL (goe374-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 374 AIRFOIL (goe374-il) Reynolds number: 50,000 Max Cl/Cd: 32.59 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe374-il-50000.txt Download as CSV file: xf-goe374-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 374 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3749 0.11184 0.10505 -0.0125 1.0000 0.0907
-8.500 -0.3792 0.11110 0.10443 -0.0149 1.0000 0.0931
-8.250 -0.3838 0.11017 0.10362 -0.0170 1.0000 0.0937
-8.000 -0.3634 0.10301 0.09640 -0.0146 1.0000 0.0996
-7.750 -0.3619 0.10065 0.09413 -0.0152 1.0000 0.1037
-7.500 -0.3659 0.09940 0.09301 -0.0175 1.0000 0.1063
-7.250 -0.3679 0.09891 0.09260 -0.0231 1.0000 0.1075
-7.000 -0.3533 0.09221 0.08596 -0.0174 1.0000 0.1140
-6.750 -0.3507 0.09021 0.08403 -0.0201 1.0000 0.1195
-6.500 -0.3475 0.08822 0.08212 -0.0243 1.0000 0.1223
-6.250 -0.3387 0.08374 0.07771 -0.0206 1.0000 0.1307
-6.000 -0.3335 0.08253 0.07652 -0.0267 1.0000 0.1362
-5.750 -0.3266 0.07808 0.07217 -0.0225 1.0000 0.1462
-5.250 -0.3123 0.07234 0.06652 -0.0247 1.0000 0.1666
-4.750 -0.2980 0.06652 0.06077 -0.0235 1.0000 0.1965
-4.500 0.0252 0.03932 0.03289 -0.0216 1.0000 1.0000
-4.250 0.0357 0.03751 0.03115 -0.0223 1.0000 1.0000
-4.000 0.0462 0.03580 0.02952 -0.0229 1.0000 1.0000
-3.750 0.0562 0.03411 0.02790 -0.0234 1.0000 1.0000
-3.500 0.0660 0.03256 0.02642 -0.0238 1.0000 1.0000
-3.250 -0.1755 0.04377 0.03855 0.0248 1.0000 0.8280
-2.500 -0.3232 0.04459 0.04010 0.0298 1.0000 0.6189
-2.250 -0.3285 0.04243 0.03806 0.0372 1.0000 0.6652
-2.000 -0.3298 0.04019 0.03590 0.0430 1.0000 0.7013
-1.750 -0.3256 0.03810 0.03387 0.0449 1.0000 0.7246
-1.500 -0.3131 0.03576 0.03157 0.0440 1.0000 0.7399
-1.250 -0.2811 0.03325 0.02901 0.0374 1.0000 0.7386
-1.000 -0.0261 0.03167 0.02437 -0.0317 1.0000 0.3167
-0.750 0.0101 0.03130 0.02320 -0.0336 1.0000 0.2468
-0.500 0.0354 0.03075 0.02220 -0.0337 1.0000 0.2123
-0.250 0.1049 0.02973 0.02051 -0.0408 0.9826 0.1848
0.000 0.1697 0.02905 0.01915 -0.0468 0.9612 0.1634
0.250 0.2376 0.02793 0.01767 -0.0534 0.9416 0.1570
0.500 0.2983 0.02714 0.01660 -0.0587 0.9187 0.1596
0.750 0.3650 0.02623 0.01554 -0.0648 0.8986 0.1611
1.000 0.4174 0.02560 0.01484 -0.0686 0.8749 0.1685
1.250 0.4741 0.02469 0.01411 -0.0728 0.8542 0.2086
1.500 0.5334 0.02261 0.01357 -0.0772 0.8317 1.0000
1.750 0.5733 0.02263 0.01320 -0.0778 0.8092 1.0000
2.000 0.6072 0.02271 0.01298 -0.0775 0.7867 1.0000
2.250 0.6362 0.02294 0.01299 -0.0767 0.7645 1.0000
2.500 0.6655 0.02311 0.01298 -0.0758 0.7439 1.0000
2.750 0.6920 0.02342 0.01318 -0.0747 0.7237 1.0000
3.000 0.7174 0.02382 0.01346 -0.0735 0.7038 1.0000
3.250 0.7443 0.02411 0.01363 -0.0724 0.6859 1.0000
3.500 0.7683 0.02467 0.01413 -0.0712 0.6673 1.0000
3.750 0.7918 0.02530 0.01472 -0.0699 0.6486 1.0000
4.000 0.8163 0.02589 0.01531 -0.0687 0.6310 1.0000
4.250 0.8413 0.02644 0.01580 -0.0674 0.6137 1.0000
4.500 0.8624 0.02728 0.01667 -0.0661 0.5941 1.0000
4.750 0.8853 0.02782 0.01719 -0.0644 0.5737 1.0000
5.000 0.9086 0.02828 0.01768 -0.0627 0.5534 1.0000
5.250 0.9299 0.02892 0.01836 -0.0611 0.5322 1.0000
5.500 0.9547 0.02929 0.01869 -0.0596 0.5133 1.0000
5.750 0.9745 0.03017 0.01969 -0.0581 0.4926 1.0000
6.000 0.9979 0.03075 0.02029 -0.0566 0.4729 1.0000
6.250 1.0195 0.03159 0.02125 -0.0551 0.4528 1.0000
6.500 1.0403 0.03265 0.02243 -0.0537 0.4326 1.0000
6.750 1.0647 0.03345 0.02321 -0.0524 0.4135 1.0000
7.000 1.0810 0.03503 0.02503 -0.0508 0.3929 1.0000
7.250 1.1011 0.03636 0.02648 -0.0494 0.3748 1.0000
7.500 1.1200 0.03807 0.02844 -0.0482 0.3598 1.0000
7.750 1.1367 0.04003 0.03065 -0.0470 0.3462 1.0000
8.000 1.1517 0.04214 0.03304 -0.0457 0.3341 1.0000
8.250 1.1683 0.04413 0.03527 -0.0445 0.3237 1.0000
8.500 1.1888 0.04529 0.03660 -0.0433 0.3116 1.0000
8.750 1.2186 0.04235 0.03353 -0.0411 0.2840 1.0000
9.000 1.2376 0.04288 0.03427 -0.0395 0.2700 1.0000
9.250 1.2527 0.04298 0.03464 -0.0375 0.2524 1.0000
9.500 1.2711 0.04096 0.03259 -0.0350 0.2258 1.0000
9.750 1.2759 0.03985 0.03153 -0.0316 0.1949 1.0000
10.000 1.2728 0.04029 0.03182 -0.0277 0.1615 1.0000
10.250 1.2616 0.04282 0.03424 -0.0239 0.1301 1.0000
10.500 1.2537 0.04557 0.03682 -0.0207 0.1096 1.0000
10.750 1.2494 0.04840 0.03971 -0.0180 0.0974 1.0000
11.000 1.2480 0.05153 0.04300 -0.0158 0.0890 1.0000
11.250 1.2539 0.05433 0.04568 -0.0141 0.0822 1.0000
11.500 1.2511 0.05821 0.05000 -0.0126 0.0789 1.0000
11.750 1.2464 0.06215 0.05424 -0.0115 0.0764 1.0000
12.000 1.2403 0.06626 0.05859 -0.0109 0.0744 1.0000
12.250 1.2312 0.07077 0.06333 -0.0110 0.0735 1.0000
12.500 1.2177 0.07587 0.06865 -0.0119 0.0728 1.0000
12.750 1.1843 0.08378 0.07692 -0.0159 0.0748 1.0000
13.000 1.1469 0.09358 0.08696 -0.0221 0.0776 1.0000
13.250 1.1154 0.10372 0.09722 -0.0283 0.0799 1.0000
13.500 1.0910 0.11342 0.10690 -0.0338 0.0815 1.0000
13.750 1.0712 0.12286 0.11634 -0.0388 0.0825 1.0000
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