GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 427 AIRFOIL (goe427-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.79 at α=1.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe427-il-1000000.txt Download as CSV file: xf-goe427-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3546 0.10170 0.10011 -0.0208 1.0000 0.0067
-8.500 -0.3559 0.09956 0.09800 -0.0198 1.0000 0.0067
-8.250 -0.3597 0.09753 0.09599 -0.0185 1.0000 0.0067
-8.000 -0.3549 0.09291 0.09139 -0.0208 0.9990 0.0069
-7.750 -0.3395 0.08996 0.08844 -0.0236 0.9974 0.0073
-7.500 -0.3212 0.08637 0.08484 -0.0285 0.9951 0.0075
-7.250 -0.2997 0.08271 0.08118 -0.0338 0.9924 0.0083
-7.000 -0.2768 0.07857 0.07703 -0.0399 0.9893 0.0089
-6.750 -0.2450 0.07416 0.07260 -0.0486 0.9866 0.0099
-6.500 -0.2111 0.06979 0.06821 -0.0577 0.9847 0.0100
-6.250 -0.1776 0.06517 0.06356 -0.0658 0.9834 0.0101
-6.000 -0.1520 0.06118 0.05953 -0.0710 0.9788 0.0101
-5.750 -0.1193 0.05665 0.05497 -0.0777 0.9758 0.0101
-4.000 0.1222 0.02606 0.02361 -0.1132 0.9476 0.0137
-3.750 0.1508 0.01165 0.00782 -0.1149 0.9389 0.0127
-3.500 0.1769 0.01018 0.00601 -0.1144 0.9315 0.0141
-3.250 0.2043 0.00984 0.00556 -0.1141 0.9240 0.0148
-3.000 0.2308 0.00853 0.00399 -0.1138 0.9150 0.0169
-2.750 0.2577 0.00854 0.00395 -0.1135 0.9022 0.0187
-2.500 0.2848 0.00858 0.00393 -0.1131 0.8871 0.0206
-2.250 0.3105 0.00780 0.00296 -0.1125 0.8713 0.0226
-2.000 0.3368 0.00757 0.00266 -0.1121 0.8562 0.0251
-1.750 0.3632 0.00752 0.00254 -0.1117 0.8409 0.0276
-1.500 0.3895 0.00740 0.00233 -0.1112 0.8260 0.0296
-1.250 0.4158 0.00738 0.00223 -0.1107 0.8114 0.0308
-1.000 0.4410 0.00689 0.00163 -0.1101 0.7970 0.0334
-0.750 0.4665 0.00671 0.00136 -0.1096 0.7813 0.0352
-0.500 0.4917 0.00664 0.00118 -0.1089 0.7617 0.0363
-0.250 0.5162 0.00663 0.00104 -0.1080 0.7326 0.0376
0.000 0.5409 0.00665 0.00094 -0.1073 0.7053 0.0400
0.250 0.5664 0.00666 0.00085 -0.1067 0.6817 0.0426
0.500 0.5911 0.00674 0.00080 -0.1060 0.6499 0.0451
0.750 0.6148 0.00688 0.00076 -0.1051 0.6016 0.0545
1.000 0.6379 0.00700 0.00086 -0.1042 0.5562 0.1257
1.250 0.6621 0.00707 0.00097 -0.1036 0.5275 0.2028
1.750 0.7220 0.00588 0.00131 -0.1053 0.4846 1.0000
2.000 0.7468 0.00609 0.00138 -0.1047 0.4573 1.0000
2.250 0.7709 0.00635 0.00147 -0.1039 0.4188 1.0000
2.500 0.7935 0.00676 0.00162 -0.1030 0.3617 1.0000
2.750 0.8150 0.00730 0.00183 -0.1019 0.2973 1.0000
3.000 0.8345 0.00810 0.00216 -0.1005 0.1987 1.0000
3.250 0.8527 0.00908 0.00263 -0.0990 0.0889 1.0000
3.500 0.8756 0.00957 0.00292 -0.0981 0.0460 1.0000
3.750 0.9005 0.00981 0.00312 -0.0976 0.0382 1.0000
4.000 0.9256 0.01002 0.00336 -0.0971 0.0356 1.0000
4.250 0.9504 0.01028 0.00366 -0.0965 0.0336 1.0000
4.500 0.9746 0.01060 0.00400 -0.0958 0.0311 1.0000
4.750 0.9985 0.01096 0.00439 -0.0951 0.0288 1.0000
5.000 1.0215 0.01143 0.00495 -0.0942 0.0265 1.0000
5.250 1.0450 0.01180 0.00537 -0.0934 0.0251 1.0000
5.500 1.0696 0.01202 0.00560 -0.0929 0.0241 1.0000
5.750 1.0938 0.01230 0.00591 -0.0923 0.0221 1.0000
6.000 1.1177 0.01259 0.00619 -0.0917 0.0195 1.0000
6.250 1.1369 0.01342 0.00711 -0.0903 0.0164 1.0000
6.500 1.1623 0.01352 0.00721 -0.0899 0.0152 1.0000
6.750 1.1863 0.01377 0.00747 -0.0893 0.0135 1.0000
7.000 1.2080 0.01427 0.00796 -0.0883 0.0116 1.0000
7.250 1.2267 0.01509 0.00888 -0.0868 0.0104 1.0000
7.500 1.2493 0.01544 0.00928 -0.0860 0.0096 1.0000
7.750 1.2708 0.01592 0.00979 -0.0850 0.0087 1.0000
8.000 1.2911 0.01648 0.01039 -0.0839 0.0080 1.0000
8.250 1.3044 0.01777 0.01180 -0.0815 0.0072 1.0000
8.500 1.3134 0.01960 0.01382 -0.0784 0.0068 1.0000
8.750 1.3311 0.02044 0.01476 -0.0768 0.0066 1.0000
9.000 1.3480 0.02136 0.01578 -0.0752 0.0063 1.0000
9.250 1.3643 0.02233 0.01687 -0.0734 0.0059 1.0000
9.500 1.3803 0.02326 0.01790 -0.0718 0.0055 1.0000
9.750 1.3966 0.02399 0.01871 -0.0702 0.0052 1.0000
10.000 1.4107 0.02478 0.01957 -0.0683 0.0049 1.0000
10.250 1.4208 0.02584 0.02074 -0.0657 0.0047 1.0000
10.500 1.4262 0.02756 0.02262 -0.0625 0.0045 1.0000
10.750 1.4257 0.03023 0.02555 -0.0587 0.0044 1.0000
11.000 1.4199 0.03361 0.02925 -0.0546 0.0043 1.0000
11.250 1.4047 0.03795 0.03397 -0.0499 0.0042 1.0000
11.500 1.3821 0.04277 0.03917 -0.0454 0.0041 1.0000
11.750 1.3733 0.04570 0.04230 -0.0427 0.0042 1.0000
12.000 1.3469 0.05101 0.04791 -0.0400 0.0041 1.0000
12.250 1.3329 0.05496 0.05206 -0.0388 0.0041 1.0000
13.250 1.1850 0.07455 0.07232 -0.0423 0.0043 1.0000
13.500 1.1637 0.08256 0.08049 -0.0457 0.0043 1.0000
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Polar data table (+)
Polar graphs
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