GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 427 AIRFOIL (goe427-il) Reynolds number: 200,000 Max Cl/Cd: 86.24 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe427-il-200000-n5.txt Download as CSV file: xf-goe427-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 427 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3235 0.10099 0.09763 -0.0232 1.0000 0.0181
-7.750 -0.3296 0.09995 0.09666 -0.0216 1.0000 0.0183
-7.500 -0.3384 0.09903 0.09581 -0.0193 1.0000 0.0185
-7.250 -0.3199 0.09594 0.09273 -0.0255 0.9959 0.0187
-7.000 -0.2951 0.09211 0.08889 -0.0328 0.9910 0.0189
-6.750 -0.2672 0.08797 0.08473 -0.0405 0.9870 0.0190
-6.500 -0.2420 0.08386 0.08059 -0.0463 0.9815 0.0191
-6.250 -0.2121 0.07937 0.07607 -0.0531 0.9780 0.0191
-6.000 -0.1868 0.07525 0.07192 -0.0583 0.9717 0.0191
-4.750 -0.0330 0.05341 0.04976 -0.0860 0.9472 0.0192
-4.500 -0.0115 0.04834 0.04465 -0.0891 0.9433 0.0167
-4.250 0.0315 0.04367 0.03984 -0.0962 0.9408 0.0157
-4.000 0.0639 0.03984 0.03587 -0.1000 0.9327 0.0152
-3.750 0.1071 0.03532 0.03112 -0.1057 0.9289 0.0150
-3.500 0.1443 0.03119 0.02673 -0.1093 0.9222 0.0160
-3.250 0.1849 0.02629 0.02142 -0.1128 0.9168 0.0178
-3.000 0.2254 0.02064 0.01510 -0.1158 0.9136 0.0185
-2.750 0.2535 0.01742 0.01123 -0.1160 0.9056 0.0203
-2.500 0.2856 0.01687 0.01057 -0.1171 0.9007 0.0245
-2.250 0.3150 0.01508 0.00825 -0.1171 0.8935 0.0281
-2.000 0.3467 0.01412 0.00696 -0.1177 0.8876 0.0334
-1.750 0.3756 0.01349 0.00618 -0.1179 0.8797 0.0377
-1.500 0.4074 0.01291 0.00540 -0.1184 0.8730 0.0418
-1.250 0.4356 0.01210 0.00447 -0.1184 0.8639 0.0446
-1.000 0.4655 0.01160 0.00392 -0.1187 0.8552 0.0479
-0.750 0.4956 0.01126 0.00350 -0.1190 0.8454 0.0510
-0.500 0.5244 0.01104 0.00318 -0.1190 0.8325 0.0555
-0.250 0.5530 0.01078 0.00285 -0.1189 0.8185 0.0574
0.000 0.5811 0.01060 0.00259 -0.1188 0.8040 0.0610
0.250 0.6086 0.01047 0.00244 -0.1185 0.7901 0.0694
0.500 0.6355 0.01033 0.00239 -0.1182 0.7762 0.1160
0.750 0.6618 0.01020 0.00239 -0.1179 0.7618 0.1821
1.000 0.6874 0.01001 0.00245 -0.1174 0.7470 0.3051
1.500 0.7482 0.00897 0.00249 -0.1184 0.7153 1.0000
1.750 0.7735 0.00911 0.00253 -0.1178 0.6975 1.0000
2.000 0.7979 0.00929 0.00259 -0.1169 0.6713 1.0000
2.250 0.8210 0.00952 0.00264 -0.1158 0.6345 1.0000
2.500 0.8424 0.00985 0.00269 -0.1143 0.5873 1.0000
2.750 0.8643 0.01021 0.00283 -0.1130 0.5530 1.0000
3.000 0.8870 0.01056 0.00305 -0.1120 0.5271 1.0000
3.250 0.9095 0.01092 0.00327 -0.1110 0.5001 1.0000
3.500 0.9328 0.01123 0.00351 -0.1101 0.4771 1.0000
3.750 0.9563 0.01152 0.00376 -0.1093 0.4542 1.0000
4.000 0.9792 0.01184 0.00405 -0.1084 0.4257 1.0000
4.250 1.0012 0.01222 0.00434 -0.1073 0.3903 1.0000
4.500 1.0221 0.01271 0.00467 -0.1061 0.3488 1.0000
4.750 1.0403 0.01345 0.00513 -0.1046 0.2873 1.0000
5.000 1.0533 0.01485 0.00590 -0.1024 0.1671 1.0000
5.250 1.0679 0.01619 0.00679 -0.1005 0.0815 1.0000
5.500 1.0878 0.01694 0.00748 -0.0992 0.0522 1.0000
5.750 1.1073 0.01770 0.00821 -0.0979 0.0427 1.0000
6.000 1.1271 0.01841 0.00905 -0.0966 0.0373 1.0000
6.250 1.1450 0.01931 0.01008 -0.0950 0.0321 1.0000
6.500 1.1626 0.02020 0.01116 -0.0934 0.0262 1.0000
6.750 1.1786 0.02123 0.01234 -0.0915 0.0220 1.0000
7.000 1.1958 0.02211 0.01335 -0.0898 0.0169 1.0000
7.250 1.2091 0.02335 0.01467 -0.0875 0.0140 1.0000
7.500 1.2191 0.02498 0.01642 -0.0847 0.0127 1.0000
7.750 1.2327 0.02632 0.01789 -0.0825 0.0114 1.0000
8.000 1.2484 0.02728 0.01895 -0.0808 0.0099 1.0000
8.250 1.2613 0.02847 0.02030 -0.0787 0.0090 1.0000
8.500 1.2718 0.03063 0.02258 -0.0762 0.0084 1.0000
8.750 1.2877 0.03346 0.02564 -0.0746 0.0079 1.0000
9.000 1.3049 0.03615 0.02864 -0.0732 0.0076 1.0000
9.250 1.3194 0.03909 0.03193 -0.0714 0.0073 1.0000
9.500 1.3287 0.04168 0.03486 -0.0690 0.0068 1.0000
9.750 1.3336 0.04385 0.03730 -0.0661 0.0063 1.0000
10.000 1.3354 0.04549 0.03913 -0.0632 0.0059 1.0000
10.250 1.3340 0.04769 0.04157 -0.0602 0.0056 1.0000
10.500 1.3292 0.05067 0.04484 -0.0572 0.0056 1.0000
10.750 1.3215 0.05378 0.04821 -0.0544 0.0055 1.0000
11.000 1.3109 0.05723 0.05192 -0.0520 0.0054 1.0000
11.250 1.2980 0.06115 0.05610 -0.0501 0.0054 1.0000
11.500 1.2835 0.06550 0.06072 -0.0490 0.0054 1.0000
11.750 1.2676 0.07024 0.06571 -0.0487 0.0054 1.0000
12.000 1.2506 0.07552 0.07122 -0.0493 0.0054 1.0000
12.250 1.2322 0.08159 0.07754 -0.0509 0.0054 1.0000
12.500 1.2133 0.08818 0.08434 -0.0535 0.0054 1.0000
12.750 1.1918 0.09620 0.09258 -0.0574 0.0055 1.0000
13.000 1.1703 0.10496 0.10153 -0.0623 0.0056 1.0000
13.250 1.1459 0.11563 0.11239 -0.0690 0.0058 1.0000
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Polar data table (+)
Polar graphs
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