GOE 6K AIRFOIL (goe06k-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 6K AIRFOIL (goe06k-il) Reynolds number: 50,000 Max Cl/Cd: 28.32 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe06k-il-50000-n5.txt Download as CSV file: xf-goe06k-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 6K 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4643 0.11390 0.10733 -0.0328 1.0000 0.0823
-8.250 -0.4792 0.11266 0.10622 -0.0325 1.0000 0.0827
-8.000 -0.4931 0.11116 0.10484 -0.0325 1.0000 0.0829
-7.750 -0.4756 0.10471 0.09838 -0.0290 1.0000 0.0853
-7.500 -0.4771 0.10172 0.09545 -0.0271 1.0000 0.0876
-7.250 -0.4831 0.09923 0.09301 -0.0259 1.0000 0.0893
-7.000 -0.4885 0.09659 0.09043 -0.0256 1.0000 0.0917
-6.750 -0.4965 0.09417 0.08808 -0.0270 1.0000 0.0954
-6.500 -0.5060 0.09259 0.08648 -0.0319 1.0000 0.0974
-6.250 -0.5010 0.08762 0.08160 -0.0279 1.0000 0.0995
-6.000 -0.4978 0.08430 0.07831 -0.0257 1.0000 0.1040
-5.750 -0.4984 0.08229 0.07608 -0.0315 1.0000 0.1121
-5.500 -0.4937 0.07767 0.07163 -0.0273 1.0000 0.1153
-5.250 -0.4889 0.07472 0.06856 -0.0293 1.0000 0.1276
-5.000 -0.4826 0.07119 0.06509 -0.0264 1.0000 0.1342
-4.500 -0.4346 0.05988 0.05299 -0.0325 1.0000 0.0539
-4.000 -0.3980 0.05185 0.04424 -0.0329 1.0000 0.0431
-3.750 -0.3811 0.04839 0.04052 -0.0325 1.0000 0.0413
-3.500 -0.3612 0.04501 0.03673 -0.0321 1.0000 0.0397
-3.250 -0.3398 0.04187 0.03308 -0.0315 1.0000 0.0388
-3.000 -0.3185 0.03930 0.03004 -0.0306 1.0000 0.0398
-2.750 -0.2963 0.03697 0.02720 -0.0297 1.0000 0.0409
-2.500 -0.2730 0.03472 0.02438 -0.0285 1.0000 0.0420
-2.250 -0.2493 0.03272 0.02183 -0.0272 1.0000 0.0431
-2.000 -0.2258 0.03102 0.01966 -0.0261 1.0000 0.0458
-1.750 -0.2023 0.02953 0.01792 -0.0253 1.0000 0.0503
-1.500 -0.1760 0.02834 0.01623 -0.0243 1.0000 0.0563
-1.250 -0.1445 0.02718 0.01485 -0.0248 0.9982 0.0665
-1.000 -0.1118 0.02628 0.01368 -0.0257 0.9962 0.0847
-0.750 -0.0795 0.02540 0.01277 -0.0268 0.9942 0.1275
-0.500 -0.0250 0.02230 0.01223 -0.0324 0.9959 1.0000
-0.250 0.0047 0.02269 0.01204 -0.0332 0.9922 1.0000
0.000 0.0349 0.02317 0.01208 -0.0342 0.9885 1.0000
0.250 0.0635 0.02358 0.01216 -0.0350 0.9845 1.0000
0.500 0.0927 0.02404 0.01232 -0.0360 0.9805 1.0000
0.750 0.1213 0.02449 0.01255 -0.0368 0.9763 1.0000
1.000 0.1494 0.02492 0.01278 -0.0376 0.9716 1.0000
1.250 0.1802 0.02547 0.01318 -0.0389 0.9676 1.0000
1.500 0.2058 0.02582 0.01344 -0.0392 0.9618 1.0000
1.750 0.2371 0.02636 0.01390 -0.0406 0.9569 1.0000
2.000 0.2640 0.02675 0.01426 -0.0411 0.9505 1.0000
2.250 0.2951 0.02725 0.01475 -0.0425 0.9443 1.0000
2.500 0.3240 0.02769 0.01523 -0.0433 0.9375 1.0000
2.750 0.3541 0.02816 0.01575 -0.0445 0.9306 1.0000
3.000 0.3833 0.02861 0.01630 -0.0454 0.9236 1.0000
3.250 0.4132 0.02907 0.01691 -0.0464 0.9162 1.0000
3.500 0.4413 0.02951 0.01751 -0.0471 0.9083 1.0000
3.750 0.4730 0.02997 0.01821 -0.0484 0.9007 1.0000
4.000 0.4990 0.03037 0.01883 -0.0486 0.8912 1.0000
4.250 0.5361 0.03081 0.01958 -0.0508 0.8839 1.0000
4.500 0.5609 0.03115 0.02026 -0.0506 0.8724 1.0000
4.750 0.5889 0.03147 0.02094 -0.0509 0.8605 1.0000
5.000 0.6198 0.03167 0.02161 -0.0515 0.8474 1.0000
5.250 0.6808 0.02964 0.02037 -0.0540 0.8113 1.0000
5.500 0.7301 0.02578 0.01330 -0.0451 0.1296 1.0000
5.750 0.7391 0.02824 0.01523 -0.0422 0.0712 1.0000
6.000 0.7554 0.03014 0.01715 -0.0401 0.0550 1.0000
6.250 0.7802 0.03191 0.01913 -0.0394 0.0453 1.0000
6.500 0.8307 0.03436 0.02184 -0.0427 0.0369 1.0000
6.750 0.8939 0.03810 0.02616 -0.0475 0.0330 1.0000
7.000 0.9278 0.04128 0.02977 -0.0480 0.0300 1.0000
7.250 0.9541 0.04476 0.03373 -0.0473 0.0293 1.0000
7.500 0.9723 0.04830 0.03775 -0.0453 0.0290 1.0000
7.750 0.9845 0.05166 0.04157 -0.0428 0.0286 1.0000
8.000 0.9926 0.05518 0.04544 -0.0400 0.0281 1.0000
8.250 0.9954 0.05907 0.04961 -0.0369 0.0275 1.0000
8.500 0.9954 0.06231 0.05327 -0.0331 0.0273 1.0000
8.750 0.9928 0.06565 0.05697 -0.0293 0.0273 1.0000
9.000 0.9875 0.06904 0.06066 -0.0255 0.0273 1.0000
9.250 0.9816 0.07256 0.06441 -0.0222 0.0274 1.0000
9.750 0.9524 0.07828 0.07072 -0.0136 0.0282 1.0000
10.000 0.9306 0.08154 0.07425 -0.0101 0.0289 1.0000
10.250 0.9106 0.08544 0.07831 -0.0082 0.0293 1.0000
10.500 0.8905 0.08987 0.08288 -0.0077 0.0297 1.0000
10.750 0.8706 0.09504 0.08815 -0.0087 0.0306 1.0000
11.000 0.8535 0.10078 0.09394 -0.0111 0.0312 1.0000
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Polar data table (+)
Polar graphs
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