GOE 476 AIRFOIL (goe476-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 476 AIRFOIL (goe476-il) Reynolds number: 100,000 Max Cl/Cd: 49.88 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe476-il-100000-n5.txt Download as CSV file: xf-goe476-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 476 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2415 0.13181 0.12632 -0.0449 1.0000 0.0851
-11.500 -0.2483 0.13010 0.12469 -0.0448 1.0000 0.0879
-11.250 -0.2644 0.12846 0.12312 -0.0458 0.9995 0.0889
-11.000 -0.2534 0.12405 0.11870 -0.0513 0.9937 0.0891
-10.750 -0.2411 0.11976 0.11439 -0.0556 0.9871 0.0891
-9.750 -0.1953 0.09858 0.09308 -0.0715 0.9581 0.0719
-9.500 -0.1765 0.09500 0.08948 -0.0745 0.9516 0.0714
-9.250 -0.1636 0.09124 0.08571 -0.0776 0.9417 0.0710
-9.000 -0.1526 0.08677 0.08122 -0.0822 0.9326 0.0710
-8.750 -0.1493 0.08064 0.07505 -0.0894 0.9224 0.0718
-8.500 -0.1440 0.07561 0.06999 -0.0946 0.9099 0.0718
-8.250 -0.1394 0.07038 0.06471 -0.1003 0.8979 0.0717
-8.000 -0.1409 0.06446 0.05869 -0.1063 0.8850 0.0717
-7.750 -0.1687 0.05416 0.04811 -0.1137 0.8679 0.0721
-7.500 -0.1458 0.05412 0.04807 -0.1131 0.8571 0.0728
-7.250 -0.1312 0.05108 0.04488 -0.1151 0.8483 0.0738
-7.000 -0.1326 0.04698 0.04056 -0.1154 0.8354 0.0746
-6.750 -0.1337 0.04185 0.03503 -0.1158 0.8256 0.0754
-6.500 -0.1331 0.03771 0.03045 -0.1147 0.8152 0.0764
-6.250 -0.1258 0.03413 0.02632 -0.1136 0.8070 0.0782
-6.000 -0.1208 0.03085 0.02230 -0.1113 0.7973 0.0802
-5.750 -0.0941 0.02991 0.02128 -0.1114 0.7911 0.0813
-5.500 -0.0760 0.02907 0.02033 -0.1100 0.7820 0.0823
-5.250 -0.0529 0.02802 0.01908 -0.1094 0.7749 0.0837
-5.000 -0.0308 0.02701 0.01784 -0.1085 0.7678 0.0855
-4.750 -0.0106 0.02596 0.01647 -0.1073 0.7597 0.0878
-4.500 0.0154 0.02496 0.01521 -0.1069 0.7536 0.0900
-4.250 0.0370 0.02454 0.01477 -0.1058 0.7455 0.0915
-4.000 0.0617 0.02398 0.01410 -0.1051 0.7386 0.0935
-3.750 0.0894 0.02331 0.01324 -0.1049 0.7332 0.0961
-3.500 0.1105 0.02275 0.01248 -0.1036 0.7254 0.0992
-3.250 0.1361 0.02243 0.01220 -0.1031 0.7192 0.1017
-3.000 0.1640 0.02206 0.01173 -0.1029 0.7142 0.1050
-2.750 0.1858 0.02170 0.01129 -0.1017 0.7071 0.1083
-2.500 0.2116 0.02137 0.01092 -0.1011 0.7014 0.1122
-2.250 0.2401 0.02112 0.01062 -0.1011 0.6968 0.1171
-2.000 0.2622 0.02090 0.01032 -0.0998 0.6900 0.1225
-1.750 0.2869 0.02070 0.01018 -0.0991 0.6841 0.1274
-1.500 0.3151 0.02047 0.00981 -0.0989 0.6794 0.1355
-1.250 0.3386 0.02034 0.00976 -0.0980 0.6739 0.1425
-1.000 0.3621 0.02023 0.00961 -0.0971 0.6680 0.1517
-0.750 0.3883 0.02006 0.00947 -0.0966 0.6629 0.1612
-0.500 0.4168 0.01987 0.00925 -0.0966 0.6586 0.1724
-0.250 0.4371 0.01990 0.00931 -0.0951 0.6519 0.1833
0.000 0.4617 0.01979 0.00927 -0.0943 0.6464 0.1945
0.250 0.4898 0.01967 0.00913 -0.0942 0.6420 0.2079
0.500 0.5140 0.01969 0.00916 -0.0934 0.6370 0.2216
0.750 0.5365 0.01970 0.00928 -0.0924 0.6312 0.2361
1.000 0.5637 0.01964 0.00928 -0.0922 0.6262 0.2551
1.250 0.5949 0.01952 0.00920 -0.0927 0.6221 0.2816
1.500 0.6173 0.01951 0.00938 -0.0918 0.6162 0.3178
1.750 0.6385 0.01914 0.00957 -0.0907 0.6105 0.4554
2.250 0.8036 0.01850 0.00978 -0.1123 0.6015 1.0000
2.500 0.8191 0.01888 0.01017 -0.1101 0.5956 1.0000
2.750 0.8397 0.01913 0.01037 -0.1086 0.5902 1.0000
3.000 0.8647 0.01928 0.01041 -0.1079 0.5854 1.0000
3.250 0.8837 0.01955 0.01065 -0.1061 0.5795 1.0000
3.500 0.9006 0.01983 0.01093 -0.1040 0.5726 1.0000
3.750 0.9247 0.01995 0.01096 -0.1031 0.5672 1.0000
4.000 0.9444 0.02021 0.01119 -0.1015 0.5617 1.0000
4.250 0.9596 0.02056 0.01158 -0.0992 0.5552 1.0000
4.500 0.9821 0.02072 0.01168 -0.0980 0.5498 1.0000
4.750 1.0034 0.02092 0.01184 -0.0966 0.5444 1.0000
5.000 1.0160 0.02131 0.01230 -0.0939 0.5376 1.0000
5.250 1.0374 0.02149 0.01244 -0.0925 0.5321 1.0000
5.500 1.0576 0.02168 0.01261 -0.0910 0.5265 1.0000
5.750 1.0686 0.02206 0.01306 -0.0880 0.5190 1.0000
6.000 1.0908 0.02215 0.01310 -0.0867 0.5129 1.0000
6.250 1.1027 0.02251 0.01351 -0.0839 0.5059 1.0000
6.500 1.1172 0.02281 0.01384 -0.0814 0.4993 1.0000
6.750 1.1413 0.02288 0.01387 -0.0805 0.4939 1.0000
7.000 1.1460 0.02343 0.01452 -0.0766 0.4864 1.0000
7.250 1.1623 0.02367 0.01475 -0.0744 0.4798 1.0000
7.500 1.1751 0.02396 0.01507 -0.0717 0.4731 1.0000
7.750 1.1805 0.02440 0.01556 -0.0679 0.4653 1.0000
8.000 1.1994 0.02452 0.01564 -0.0662 0.4581 1.0000
8.250 1.1997 0.02519 0.01639 -0.0618 0.4494 1.0000
8.500 1.2188 0.02531 0.01646 -0.0601 0.4413 1.0000
8.750 1.2177 0.02614 0.01740 -0.0559 0.4315 1.0000
9.000 1.2321 0.02646 0.01768 -0.0538 0.4224 1.0000
9.250 1.2335 0.02732 0.01862 -0.0503 0.4114 1.0000
9.500 1.2388 0.02809 0.01941 -0.0474 0.4000 1.0000
9.750 1.2474 0.02874 0.02004 -0.0449 0.3882 1.0000
10.000 1.2454 0.03001 0.02136 -0.0416 0.3740 1.0000
10.250 1.2445 0.03137 0.02276 -0.0387 0.3594 1.0000
10.500 1.2438 0.03283 0.02422 -0.0361 0.3433 1.0000
10.750 1.2434 0.03440 0.02576 -0.0337 0.3264 1.0000
11.000 1.2432 0.03604 0.02735 -0.0315 0.3092 1.0000
11.250 1.2438 0.03773 0.02897 -0.0296 0.2937 1.0000
11.500 1.2446 0.03949 0.03065 -0.0278 0.2799 1.0000
11.750 1.2460 0.04129 0.03238 -0.0261 0.2680 1.0000
12.000 1.2482 0.04305 0.03403 -0.0245 0.2577 1.0000
12.250 1.2511 0.04491 0.03589 -0.0232 0.2482 1.0000
12.500 1.2554 0.04660 0.03751 -0.0219 0.2400 1.0000
12.750 1.2586 0.04853 0.03947 -0.0208 0.2316 1.0000
13.000 1.2643 0.05013 0.04098 -0.0196 0.2245 1.0000
13.250 1.2678 0.05217 0.04313 -0.0188 0.2172 1.0000
13.500 1.2731 0.05395 0.04489 -0.0178 0.2106 1.0000
13.750 1.2793 0.05568 0.04665 -0.0170 0.2048 1.0000
14.000 1.2831 0.05778 0.04886 -0.0163 0.1985 1.0000
14.250 1.2889 0.05957 0.05064 -0.0156 0.1927 1.0000
14.500 1.2924 0.06177 0.05293 -0.0151 0.1869 1.0000
14.750 1.2946 0.06413 0.05539 -0.0146 0.1808 1.0000
15.000 1.2987 0.06618 0.05740 -0.0141 0.1752 1.0000
15.250 1.2982 0.06903 0.06045 -0.0139 0.1687 1.0000
15.500 1.2993 0.07160 0.06307 -0.0137 0.1630 1.0000
15.750 1.3000 0.07431 0.06586 -0.0136 0.1572 1.0000
16.000 1.2991 0.07727 0.06893 -0.0137 0.1511 1.0000
16.250 1.2988 0.08013 0.07179 -0.0137 0.1456 1.0000
16.500 1.2965 0.08342 0.07522 -0.0140 0.1393 1.0000
16.750 1.2947 0.08654 0.07832 -0.0142 0.1339 1.0000
17.000 1.2920 0.08999 0.08191 -0.0147 0.1279 1.0000
17.250 1.2897 0.09331 0.08526 -0.0151 0.1229 1.0000
17.500 1.2880 0.09659 0.08858 -0.0156 0.1181 1.0000
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