GOE 6K AIRFOIL (goe06k-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 6K AIRFOIL (goe06k-il) Reynolds number: 500,000 Max Cl/Cd: 116.52 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe06k-il-500000-n5.txt Download as CSV file: xf-goe06k-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3347 0.08452 0.08222 -0.0653 0.9806 0.0067
-8.000 -0.3239 0.07978 0.07750 -0.0708 0.9786 0.0067
-7.750 -0.3225 0.07681 0.07453 -0.0724 0.9722 0.0067
-6.750 -0.2223 0.03835 0.03606 -0.0924 0.9481 0.0067
-6.250 -0.2428 0.04767 0.04501 -0.0972 0.9456 0.0045
-6.000 -0.2220 0.04208 0.03922 -0.1000 0.9432 0.0045
-5.750 -0.1986 0.03913 0.03613 -0.1021 0.9418 0.0057
-5.500 -0.1893 0.03494 0.03171 -0.1001 0.9348 0.0052
-5.250 -0.1681 0.03130 0.02781 -0.1002 0.9319 0.0057
-5.000 -0.1462 0.02641 0.02252 -0.0997 0.9297 0.0054
-4.500 -0.1124 0.01573 0.01046 -0.0939 0.9229 0.0047
-4.250 -0.0894 0.01387 0.00822 -0.0929 0.9200 0.0051
-4.000 -0.0616 0.01272 0.00683 -0.0930 0.9180 0.0056
-3.750 -0.0323 0.01176 0.00565 -0.0933 0.9165 0.0063
-3.500 -0.0020 0.01096 0.00470 -0.0940 0.9152 0.0073
-3.250 0.0300 0.01030 0.00394 -0.0951 0.9140 0.0084
-3.000 0.0584 0.00983 0.00340 -0.0954 0.9119 0.0102
-2.750 0.0783 0.00953 0.00304 -0.0937 0.9074 0.0120
-2.500 0.1060 0.00916 0.00261 -0.0938 0.9046 0.0156
-2.250 0.1364 0.00886 0.00229 -0.0946 0.9025 0.0260
-2.000 0.1683 0.00863 0.00211 -0.0957 0.9007 0.0493
-1.750 0.2015 0.00845 0.00192 -0.0972 0.8992 0.0638
-1.500 0.2250 0.00830 0.00182 -0.0964 0.8956 0.0864
-1.250 0.2452 0.00784 0.00174 -0.0951 0.8913 0.2218
-1.000 0.2696 0.00736 0.00167 -0.0948 0.8880 0.3711
-0.750 0.2919 0.00664 0.00163 -0.0940 0.8852 0.6038
-0.500 0.3969 0.00594 0.00194 -0.1121 0.8911 0.9385
-0.250 0.4365 0.00603 0.00200 -0.1149 0.8892 0.9634
0.000 0.4758 0.00614 0.00208 -0.1176 0.8875 0.9838
0.250 0.5336 0.00621 0.00215 -0.1248 0.8875 0.9961
0.500 0.5843 0.00614 0.00207 -0.1303 0.8836 1.0000
0.750 0.6043 0.00614 0.00206 -0.1286 0.8731 1.0000
1.000 0.6292 0.00615 0.00207 -0.1280 0.8656 1.0000
1.250 0.6539 0.00615 0.00208 -0.1275 0.8577 1.0000
1.500 0.6757 0.00617 0.00210 -0.1261 0.8460 1.0000
1.750 0.6987 0.00617 0.00208 -0.1250 0.8274 1.0000
2.000 0.7180 0.00622 0.00207 -0.1230 0.7997 1.0000
2.250 0.7376 0.00633 0.00208 -0.1211 0.7678 1.0000
2.500 0.7506 0.00660 0.00214 -0.1176 0.7140 1.0000
2.750 0.7411 0.00740 0.00233 -0.1091 0.5808 1.0000
3.000 0.7280 0.00860 0.00277 -0.1004 0.4252 1.0000
3.250 0.7232 0.00988 0.00325 -0.0938 0.2498 1.0000
3.500 0.7287 0.01086 0.00368 -0.0895 0.1243 1.0000
3.750 0.7406 0.01155 0.00408 -0.0864 0.0571 1.0000
4.000 0.7554 0.01211 0.00446 -0.0838 0.0175 1.0000
4.250 0.7727 0.01251 0.00489 -0.0817 0.0120 1.0000
4.500 0.7894 0.01294 0.00536 -0.0794 0.0090 1.0000
4.750 0.8058 0.01339 0.00586 -0.0771 0.0074 1.0000
5.000 0.8218 0.01390 0.00644 -0.0747 0.0066 1.0000
5.250 0.8377 0.01442 0.00702 -0.0723 0.0057 1.0000
5.500 0.8531 0.01503 0.00768 -0.0699 0.0050 1.0000
5.750 0.8685 0.01570 0.00846 -0.0674 0.0046 1.0000
6.000 0.8835 0.01658 0.00944 -0.0649 0.0043 1.0000
6.250 0.9008 0.01747 0.01042 -0.0629 0.0040 1.0000
6.500 0.9201 0.01859 0.01164 -0.0614 0.0037 1.0000
6.750 0.9480 0.02050 0.01373 -0.0618 0.0036 1.0000
7.000 0.9791 0.02295 0.01659 -0.0622 0.0034 1.0000
7.250 1.0020 0.02447 0.01842 -0.0612 0.0027 1.0000
7.500 1.0238 0.02787 0.02227 -0.0598 0.0026 1.0000
7.750 1.0376 0.03111 0.02591 -0.0569 0.0026 1.0000
8.000 1.0429 0.03655 0.03190 -0.0519 0.0026 1.0000
8.250 1.0445 0.04069 0.03640 -0.0470 0.0026 1.0000
8.500 1.0385 0.04634 0.04246 -0.0407 0.0028 1.0000
8.750 1.0317 0.05062 0.04702 -0.0352 0.0029 1.0000
9.000 1.0223 0.05456 0.05120 -0.0298 0.0029 1.0000
9.250 1.0111 0.05792 0.05475 -0.0246 0.0030 1.0000
9.500 0.9939 0.06104 0.05803 -0.0188 0.0031 1.0000
9.750 0.9767 0.06426 0.06140 -0.0139 0.0032 1.0000
10.000 0.9620 0.06702 0.06427 -0.0104 0.0033 1.0000
10.250 0.9429 0.07065 0.06803 -0.0073 0.0033 1.0000
10.500 0.9227 0.07475 0.07225 -0.0055 0.0033 1.0000
10.750 0.9038 0.07923 0.07683 -0.0050 0.0033 1.0000
11.000 0.8838 0.08474 0.08244 -0.0063 0.0033 1.0000
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Polar data table (+)
Polar graphs
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