GOE 144 (MVA H.21) AIRFOIL (goe144-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 144 (MVA H.21) AIRFOIL (goe144-il) Reynolds number: 500,000 Max Cl/Cd: 98.21 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe144-il-500000-n5.txt Download as CSV file: xf-goe144-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 144 (MVA H.21) 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3618 0.09198 0.08981 -0.0260 1.0000 0.0070
-8.500 -0.3676 0.08840 0.08627 -0.0260 1.0000 0.0069
-8.000 -0.4066 0.02919 0.02614 -0.0923 0.9705 0.0072
-7.750 -0.3801 0.02074 0.01702 -0.0983 0.9664 0.0075
-7.500 -0.3543 0.01872 0.01474 -0.0991 0.9608 0.0080
-7.250 -0.3259 0.01706 0.01280 -0.1001 0.9567 0.0087
-7.000 -0.2943 0.01584 0.01132 -0.1015 0.9539 0.0092
-6.750 -0.2657 0.01442 0.00964 -0.1022 0.9488 0.0101
-6.500 -0.2341 0.01359 0.00867 -0.1032 0.9442 0.0111
-6.250 -0.2001 0.01293 0.00787 -0.1047 0.9402 0.0123
-6.000 -0.1682 0.01234 0.00713 -0.1056 0.9346 0.0136
-5.750 -0.1355 0.01177 0.00651 -0.1067 0.9291 0.0160
-5.500 -0.1015 0.01144 0.00610 -0.1080 0.9237 0.0186
-5.250 -0.0708 0.01115 0.00569 -0.1085 0.9164 0.0206
-4.750 -0.0108 0.01030 0.00461 -0.1093 0.9012 0.0255
-4.500 0.0183 0.01002 0.00422 -0.1095 0.8927 0.0276
-4.250 0.0462 0.00978 0.00387 -0.1093 0.8827 0.0296
-4.000 0.0733 0.00956 0.00354 -0.1090 0.8716 0.0308
-3.750 0.1004 0.00938 0.00327 -0.1086 0.8580 0.0316
-3.500 0.1269 0.00908 0.00285 -0.1081 0.8404 0.0340
-3.250 0.1529 0.00886 0.00252 -0.1075 0.8103 0.0370
-3.000 0.1771 0.00881 0.00221 -0.1064 0.7589 0.0396
-2.750 0.2009 0.00883 0.00203 -0.1053 0.7225 0.0450
-2.500 0.2260 0.00883 0.00198 -0.1046 0.6995 0.0610
-2.250 0.2517 0.00888 0.00190 -0.1039 0.6805 0.0666
-2.000 0.2776 0.00890 0.00183 -0.1034 0.6635 0.0719
-1.750 0.3037 0.00894 0.00176 -0.1029 0.6479 0.0752
-1.500 0.3299 0.00896 0.00168 -0.1024 0.6335 0.0773
-1.250 0.3560 0.00894 0.00160 -0.1019 0.6181 0.0802
-1.000 0.3819 0.00894 0.00154 -0.1014 0.6015 0.0839
-0.750 0.4078 0.00897 0.00149 -0.1009 0.5846 0.0878
-0.500 0.4337 0.00900 0.00145 -0.1004 0.5686 0.0916
-0.250 0.4597 0.00902 0.00144 -0.0999 0.5536 0.0979
0.000 0.4856 0.00904 0.00147 -0.0995 0.5388 0.1140
0.250 0.5118 0.00910 0.00150 -0.0990 0.5255 0.1267
0.500 0.5381 0.00917 0.00153 -0.0986 0.5142 0.1350
1.000 0.5906 0.00931 0.00159 -0.0978 0.4894 0.1462
1.250 0.6169 0.00938 0.00163 -0.0974 0.4769 0.1511
1.500 0.6433 0.00946 0.00167 -0.0970 0.4674 0.1545
2.000 0.6957 0.00960 0.00179 -0.0962 0.4452 0.1639
2.250 0.7219 0.00969 0.00187 -0.0958 0.4335 0.1681
2.500 0.7480 0.00977 0.00195 -0.0954 0.4223 0.1732
2.750 0.7739 0.00987 0.00204 -0.0950 0.4111 0.1796
3.000 0.7999 0.00997 0.00216 -0.0946 0.3998 0.1873
3.250 0.8256 0.01007 0.00228 -0.0942 0.3864 0.2011
3.500 0.8510 0.01017 0.00244 -0.0937 0.3709 0.2373
3.750 0.8764 0.01027 0.00261 -0.0932 0.3567 0.2801
4.000 0.9004 0.01012 0.00281 -0.0927 0.3418 0.4689
4.500 0.9575 0.00975 0.00328 -0.0934 0.2907 1.0000
4.750 0.9783 0.01039 0.00363 -0.0922 0.2403 1.0000
5.000 1.0013 0.01081 0.00392 -0.0914 0.2140 1.0000
5.250 1.0234 0.01132 0.00425 -0.0905 0.1804 1.0000
5.500 1.0409 0.01231 0.00483 -0.0889 0.1085 1.0000
5.750 1.0624 0.01287 0.00528 -0.0879 0.0869 1.0000
6.000 1.0847 0.01335 0.00568 -0.0870 0.0690 1.0000
6.250 1.1016 0.01438 0.00644 -0.0852 0.0191 1.0000
6.500 1.1240 0.01483 0.00695 -0.0842 0.0138 1.0000
6.750 1.1468 0.01521 0.00739 -0.0833 0.0125 1.0000
7.000 1.1688 0.01566 0.00793 -0.0823 0.0112 1.0000
7.250 1.1901 0.01617 0.00851 -0.0812 0.0101 1.0000
7.500 1.2085 0.01696 0.00941 -0.0796 0.0088 1.0000
7.750 1.2295 0.01744 0.00995 -0.0785 0.0082 1.0000
8.000 1.2492 0.01802 0.01060 -0.0772 0.0076 1.0000
8.250 1.2678 0.01868 0.01133 -0.0757 0.0070 1.0000
8.500 1.2852 0.01939 0.01213 -0.0741 0.0066 1.0000
8.750 1.3014 0.02016 0.01296 -0.0723 0.0063 1.0000
9.000 1.3144 0.02112 0.01400 -0.0700 0.0060 1.0000
9.250 1.3220 0.02232 0.01531 -0.0669 0.0057 1.0000
9.500 1.3326 0.02314 0.01622 -0.0643 0.0055 1.0000
9.750 1.3437 0.02392 0.01709 -0.0617 0.0052 1.0000
10.000 1.3520 0.02488 0.01813 -0.0590 0.0049 1.0000
10.250 1.3599 0.02589 0.01923 -0.0563 0.0046 1.0000
10.500 1.3651 0.02711 0.02054 -0.0535 0.0045 1.0000
10.750 1.3693 0.02845 0.02199 -0.0508 0.0044 1.0000
11.000 1.3729 0.02992 0.02354 -0.0484 0.0043 1.0000
11.250 1.3761 0.03151 0.02523 -0.0461 0.0042 1.0000
11.500 1.3782 0.03328 0.02713 -0.0441 0.0041 1.0000
11.750 1.3788 0.03531 0.02925 -0.0424 0.0040 1.0000
12.000 1.3758 0.03785 0.03189 -0.0407 0.0038 1.0000
12.250 1.3720 0.04070 0.03486 -0.0394 0.0038 1.0000
12.500 1.3703 0.04352 0.03782 -0.0386 0.0037 1.0000
12.750 1.3687 0.04650 0.04093 -0.0380 0.0037 1.0000
13.000 1.3676 0.04955 0.04413 -0.0378 0.0036 1.0000
13.250 1.3648 0.05293 0.04767 -0.0376 0.0035 1.0000
13.500 1.3615 0.05648 0.05135 -0.0377 0.0035 1.0000
13.750 1.3574 0.06025 0.05528 -0.0381 0.0035 1.0000
14.000 1.3515 0.06442 0.05962 -0.0386 0.0034 1.0000
14.250 1.3453 0.06875 0.06412 -0.0394 0.0033 1.0000
14.500 1.3375 0.07348 0.06902 -0.0405 0.0033 1.0000
14.750 1.3287 0.07855 0.07427 -0.0420 0.0033 1.0000
15.000 1.3197 0.08383 0.07972 -0.0439 0.0032 1.0000
15.250 1.3099 0.08941 0.08546 -0.0461 0.0032 1.0000
15.500 1.2972 0.09577 0.09200 -0.0488 0.0032 1.0000
15.750 1.2871 0.10187 0.09825 -0.0517 0.0031 1.0000
16.000 1.2736 0.10886 0.10542 -0.0552 0.0031 1.0000
16.250 1.2617 0.11581 0.11252 -0.0589 0.0031 1.0000
16.500 1.2490 0.12317 0.12004 -0.0630 0.0030 1.0000
16.750 1.2345 0.13122 0.12825 -0.0676 0.0031 1.0000
17.000 1.2200 0.13961 0.13679 -0.0726 0.0031 1.0000
17.250 1.2074 0.14784 0.14516 -0.0776 0.0031 1.0000
17.500 1.1925 0.15703 0.15449 -0.0832 0.0031 1.0000
17.750 1.1800 0.16591 0.16350 -0.0888 0.0031 1.0000
18.000 1.1632 0.17655 0.17426 -0.0953 0.0032 1.0000
18.250 1.1471 0.18774 0.18556 -0.1021 0.0032 1.0000
18.500 1.1287 0.20101 0.19893 -0.1097 0.0033 1.0000
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