GOE 391 AIRFOIL (goe391-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 391 AIRFOIL (goe391-il) Reynolds number: 50,000 Max Cl/Cd: 41.48 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe391-il-50000-n5.txt Download as CSV file: xf-goe391-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 391 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 -0.4156 0.09972 0.09289 -0.0227 1.0000 0.0662
-7.500 -0.4179 0.09750 0.09077 -0.0228 1.0000 0.0680
-7.250 -0.4198 0.09551 0.08887 -0.0249 1.0000 0.0706
-7.000 -0.4196 0.09401 0.08744 -0.0289 1.0000 0.0718
-6.750 -0.4153 0.09224 0.08567 -0.0330 1.0000 0.0723
-6.500 -0.4111 0.08633 0.07989 -0.0277 1.0000 0.0746
-6.250 -0.4061 0.08308 0.07667 -0.0267 1.0000 0.0774
-6.000 -0.4004 0.08015 0.07376 -0.0274 1.0000 0.0811
-5.750 -0.3878 0.07859 0.07207 -0.0340 1.0000 0.0860
-5.500 -0.3829 0.07405 0.06763 -0.0321 1.0000 0.0880
-5.250 -0.3763 0.07068 0.06431 -0.0304 1.0000 0.0932
-4.750 -0.3442 0.06582 0.05905 -0.0368 1.0000 0.1145
-4.500 -0.3412 0.06124 0.05468 -0.0330 1.0000 0.1208
-4.250 -0.3270 0.05815 0.05151 -0.0337 1.0000 0.1339
-4.000 -0.3121 0.05501 0.04829 -0.0342 1.0000 0.1489
-3.750 -0.2959 0.05205 0.04523 -0.0345 1.0000 0.1657
-3.500 -0.2491 0.04708 0.03958 -0.0389 1.0000 0.0799
-3.250 -0.2181 0.04315 0.03513 -0.0398 1.0000 0.0560
-3.000 -0.1948 0.04019 0.03187 -0.0400 1.0000 0.0546
-2.750 -0.1691 0.03757 0.02880 -0.0402 1.0000 0.0563
-2.500 -0.1437 0.03504 0.02581 -0.0400 1.0000 0.0565
-2.250 -0.1178 0.03257 0.02291 -0.0397 1.0000 0.0559
-2.000 -0.0912 0.03046 0.02029 -0.0393 1.0000 0.0565
-1.750 -0.0664 0.02867 0.01816 -0.0390 1.0000 0.0627
-1.500 -0.0403 0.02708 0.01618 -0.0384 1.0000 0.0656
-1.250 -0.0130 0.02565 0.01432 -0.0379 1.0000 0.0679
-1.000 0.0113 0.02463 0.01298 -0.0372 1.0000 0.0768
-0.750 0.0367 0.02375 0.01182 -0.0365 1.0000 0.0816
-0.500 0.0638 0.02302 0.01075 -0.0359 1.0000 0.0836
-0.250 0.0888 0.02249 0.00996 -0.0353 1.0000 0.0859
0.000 0.1128 0.02201 0.00934 -0.0347 1.0000 0.0894
0.250 0.1361 0.02173 0.00893 -0.0342 1.0000 0.0953
0.500 0.1594 0.02154 0.00865 -0.0337 1.0000 0.1043
0.750 0.1965 0.02115 0.00853 -0.0362 0.9943 0.1567
1.000 0.2365 0.01930 0.00841 -0.0391 0.9882 1.0000
1.250 0.2738 0.01977 0.00860 -0.0415 0.9796 1.0000
1.500 0.3102 0.02022 0.00887 -0.0438 0.9703 1.0000
1.750 0.3461 0.02063 0.00918 -0.0460 0.9604 1.0000
2.000 0.3836 0.02102 0.00952 -0.0484 0.9490 1.0000
2.250 0.4236 0.02131 0.00982 -0.0511 0.9352 1.0000
2.500 0.4654 0.02146 0.01005 -0.0538 0.9188 1.0000
2.750 0.5070 0.02153 0.01021 -0.0564 0.9024 1.0000
3.000 0.5450 0.02160 0.01043 -0.0582 0.8876 1.0000
3.250 0.5811 0.02168 0.01073 -0.0597 0.8735 1.0000
3.500 0.6165 0.02168 0.01095 -0.0608 0.8579 1.0000
3.750 0.6495 0.02160 0.01117 -0.0613 0.8381 1.0000
4.000 0.6863 0.02125 0.01112 -0.0618 0.8155 1.0000
4.250 0.7185 0.02086 0.01102 -0.0612 0.7857 1.0000
4.500 0.7504 0.02042 0.01087 -0.0603 0.7485 1.0000
4.750 0.7820 0.01992 0.01062 -0.0589 0.6908 1.0000
5.000 0.8154 0.01966 0.01010 -0.0571 0.5814 1.0000
5.250 0.8294 0.02072 0.01019 -0.0532 0.4041 1.0000
5.500 0.8396 0.02238 0.01105 -0.0503 0.2763 1.0000
5.750 0.8522 0.02430 0.01230 -0.0483 0.1618 1.0000
6.000 0.8690 0.02618 0.01402 -0.0466 0.1124 1.0000
6.250 0.8877 0.02785 0.01566 -0.0451 0.0956 1.0000
6.500 0.9085 0.02955 0.01754 -0.0438 0.0854 1.0000
6.750 0.9292 0.03140 0.01947 -0.0426 0.0711 1.0000
7.000 0.9530 0.03348 0.02183 -0.0416 0.0598 1.0000
7.250 0.9787 0.03624 0.02481 -0.0408 0.0518 1.0000
7.500 0.9997 0.03889 0.02770 -0.0400 0.0446 1.0000
7.750 1.0221 0.04247 0.03183 -0.0387 0.0412 1.0000
8.000 1.0386 0.04578 0.03568 -0.0369 0.0381 1.0000
8.250 1.0515 0.04887 0.03899 -0.0354 0.0348 1.0000
8.500 1.0595 0.05297 0.04348 -0.0334 0.0333 1.0000
8.750 1.0632 0.05698 0.04809 -0.0308 0.0328 1.0000
9.000 1.0627 0.06106 0.05266 -0.0282 0.0326 1.0000
9.250 1.0579 0.06519 0.05722 -0.0257 0.0324 1.0000
9.500 1.0498 0.06922 0.06159 -0.0234 0.0324 1.0000
9.750 1.0370 0.07317 0.06581 -0.0211 0.0323 1.0000
10.000 1.0207 0.07700 0.06984 -0.0190 0.0324 1.0000
10.250 1.0049 0.08105 0.07404 -0.0181 0.0326 1.0000
10.500 0.9880 0.08560 0.07872 -0.0185 0.0327 1.0000
10.750 0.9718 0.09071 0.08393 -0.0201 0.0329 1.0000
11.000 0.9569 0.09642 0.08972 -0.0228 0.0332 1.0000
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Polar data table (+)
Polar graphs
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