GOE 711 AIRFOIL (goe711-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 711 AIRFOIL (goe711-il) Reynolds number: 50,000 Max Cl/Cd: 33.23 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe711-il-50000-n5.txt Download as CSV file: xf-goe711-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 711 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 -0.3101 0.13026 0.12446 -0.0262 1.0000 0.0989
-8.250 -0.3146 0.12834 0.12259 -0.0327 0.9930 0.1020
-8.000 -0.3244 0.12661 0.12090 -0.0394 0.9838 0.1028
-7.750 -0.2855 0.11906 0.11333 -0.0377 0.9824 0.1063
-7.500 -0.2694 0.11532 0.10957 -0.0397 0.9764 0.1115
-7.250 -0.2725 0.11285 0.10714 -0.0437 0.9669 0.1171
-7.000 -0.2778 0.10977 0.10407 -0.0562 0.9529 0.1200
-6.750 -0.2488 0.10489 0.09920 -0.0493 0.9518 0.1266
-6.500 -0.2457 0.10171 0.09598 -0.0583 0.9392 0.1358
-6.250 -0.2278 0.09687 0.09116 -0.0599 0.9333 0.1396
-6.000 -0.2135 0.09357 0.08786 -0.0599 0.9250 0.1456
-5.750 -0.1980 0.08920 0.08340 -0.0678 0.9164 0.1561
-5.500 -0.1858 0.08625 0.08047 -0.0663 0.9068 0.1632
-5.250 -0.1630 0.08229 0.07645 -0.0705 0.9007 0.1790
-5.000 -0.1531 0.07931 0.07343 -0.0715 0.8894 0.1942
-4.750 -0.1374 0.07619 0.07027 -0.0729 0.8800 0.2115
-4.500 -0.1140 0.07280 0.06682 -0.0753 0.8727 0.2319
-4.000 -0.0074 0.05753 0.04956 -0.0976 0.8569 0.0862
-3.750 0.0136 0.05472 0.04665 -0.0979 0.8459 0.0845
-3.500 0.0456 0.05168 0.04329 -0.0999 0.8380 0.0822
-3.250 0.0794 0.04887 0.04008 -0.1019 0.8296 0.0802
-3.000 0.1095 0.04671 0.03754 -0.1029 0.8197 0.0807
-2.750 0.1498 0.04434 0.03469 -0.1053 0.8131 0.0820
-2.500 0.1785 0.04264 0.03262 -0.1056 0.8021 0.0817
-2.250 0.2220 0.04039 0.02995 -0.1080 0.7966 0.0813
-2.000 0.2495 0.03909 0.02834 -0.1078 0.7848 0.0813
-1.750 0.2953 0.03720 0.02604 -0.1102 0.7797 0.0828
-1.500 0.3217 0.03635 0.02490 -0.1096 0.7670 0.0851
-1.250 0.3531 0.03539 0.02365 -0.1097 0.7562 0.0866
-1.000 0.3943 0.03387 0.02195 -0.1112 0.7489 0.0878
-0.750 0.4218 0.03306 0.02103 -0.1107 0.7366 0.0894
-0.500 0.4560 0.03215 0.01997 -0.1112 0.7263 0.0919
-0.250 0.4927 0.03124 0.01890 -0.1121 0.7167 0.0976
0.000 0.5207 0.03082 0.01829 -0.1117 0.7037 0.1027
0.250 0.5514 0.03019 0.01759 -0.1120 0.6916 0.1079
0.500 0.5867 0.02953 0.01676 -0.1129 0.6807 0.1160
0.750 0.6184 0.02901 0.01618 -0.1133 0.6682 0.1332
1.000 0.6451 0.02765 0.01605 -0.1137 0.6550 0.4163
1.500 0.6983 0.02655 0.01539 -0.1114 0.6289 1.0000
1.750 0.7286 0.02661 0.01511 -0.1116 0.6164 1.0000
2.000 0.7560 0.02681 0.01502 -0.1114 0.6035 1.0000
2.250 0.7801 0.02715 0.01515 -0.1108 0.5901 1.0000
2.500 0.8052 0.02748 0.01527 -0.1104 0.5774 1.0000
2.750 0.8323 0.02776 0.01533 -0.1103 0.5657 1.0000
3.000 0.8601 0.02804 0.01539 -0.1103 0.5546 1.0000
3.250 0.8818 0.02855 0.01578 -0.1095 0.5427 1.0000
3.500 0.9070 0.02898 0.01605 -0.1092 0.5322 1.0000
3.750 0.9345 0.02932 0.01623 -0.1093 0.5224 1.0000
4.000 0.9550 0.02994 0.01678 -0.1083 0.5119 1.0000
4.250 0.9832 0.03032 0.01700 -0.1086 0.5035 1.0000
4.500 1.0034 0.03098 0.01763 -0.1077 0.4939 1.0000
4.750 1.0294 0.03147 0.01801 -0.1077 0.4860 1.0000
5.000 1.0502 0.03214 0.01867 -0.1069 0.4775 1.0000
5.250 1.0764 0.03266 0.01909 -0.1069 0.4704 1.0000
5.500 1.0947 0.03346 0.01992 -0.1058 0.4625 1.0000
5.750 1.1250 0.03386 0.02020 -0.1065 0.4566 1.0000
6.000 1.1377 0.03489 0.02134 -0.1046 0.4489 1.0000
6.250 1.1625 0.03549 0.02189 -0.1045 0.4428 1.0000
6.500 1.1827 0.03631 0.02275 -0.1038 0.4369 1.0000
6.750 1.1982 0.03730 0.02382 -0.1024 0.4306 1.0000
7.000 1.2253 0.03787 0.02435 -0.1027 0.4256 1.0000
7.250 1.2384 0.03900 0.02559 -0.1010 0.4200 1.0000
7.500 1.2513 0.04011 0.02681 -0.0993 0.4143 1.0000
7.750 1.2776 0.04073 0.02742 -0.0995 0.4097 1.0000
8.000 1.2888 0.04198 0.02878 -0.0976 0.4049 1.0000
8.250 1.2903 0.04359 0.03058 -0.0944 0.3999 1.0000
8.500 1.3087 0.04456 0.03161 -0.0936 0.3955 1.0000
8.750 1.3433 0.04493 0.03195 -0.0950 0.3918 1.0000
9.000 1.3182 0.04786 0.03518 -0.0886 0.3865 1.0000
9.250 1.3181 0.04985 0.03731 -0.0859 0.3818 1.0000
9.500 1.3409 0.05065 0.03820 -0.0857 0.3781 1.0000
9.750 1.3551 0.05203 0.03967 -0.0846 0.3746 1.0000
10.000 1.2891 0.05879 0.04677 -0.0767 0.3684 1.0000
10.250 1.2851 0.06166 0.04977 -0.0747 0.3639 1.0000
10.500 1.3194 0.06140 0.04955 -0.0752 0.3611 1.0000
10.750 1.1511 0.08275 0.07121 -0.0697 0.3467 1.0000
11.000 1.1778 0.08260 0.07115 -0.0691 0.3448 1.0000
11.500 1.1012 0.10144 0.09018 -0.0708 0.3280 1.0000
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Polar data table (+)
Polar graphs
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