GOE 134 (MVA H.12) AIRFOIL (goe134-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 134 (MVA H.12) AIRFOIL (goe134-il) Reynolds number: 50,000 Max Cl/Cd: 29.37 at α=11° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe134-il-50000.txt Download as CSV file: xf-goe134-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 134 (MVA H.12) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4017 0.10647 0.09980 -0.0182 1.0000 0.1833
-7.750 -0.3864 0.10173 0.09508 -0.0168 1.0000 0.1923
-7.500 -0.4032 0.10074 0.09425 -0.0185 1.0000 0.1989
-7.250 -0.3898 0.09645 0.08999 -0.0165 1.0000 0.2110
-7.000 -0.3880 0.09332 0.08694 -0.0160 1.0000 0.2220
-6.750 -0.4069 0.09254 0.08630 -0.0211 1.0000 0.2307
-6.500 -0.4044 0.08952 0.08335 -0.0203 1.0000 0.2461
-6.250 -0.3884 0.08494 0.07883 -0.0149 1.0000 0.2653
-6.000 -0.3835 0.08203 0.07599 -0.0127 1.0000 0.2845
-5.750 -0.3878 0.07992 0.07397 -0.0126 1.0000 0.3063
-5.500 -0.3804 0.07662 0.07076 -0.0087 1.0000 0.3292
-5.250 -0.3800 0.07412 0.06835 -0.0059 1.0000 0.3580
-5.000 -0.3753 0.07158 0.06590 -0.0011 1.0000 0.3931
-4.750 0.0163 0.04769 0.04085 -0.0245 1.0000 1.0000
-4.500 0.0274 0.04561 0.03881 -0.0255 1.0000 1.0000
-4.250 0.0382 0.04362 0.03687 -0.0264 1.0000 1.0000
-4.000 0.0488 0.04170 0.03503 -0.0272 1.0000 1.0000
-3.750 -0.0102 0.04388 0.03746 -0.0120 1.0000 0.9618
-3.500 -0.0706 0.04550 0.03937 0.0016 1.0000 0.9133
-3.250 -0.1258 0.04627 0.04044 0.0125 1.0000 0.8683
-3.000 -0.1787 0.04658 0.04104 0.0224 1.0000 0.8359
-2.750 -0.2314 0.04673 0.04147 0.0326 1.0000 0.8182
-2.500 -0.2818 0.04654 0.04153 0.0423 1.0000 0.8042
-2.250 -0.1370 0.03778 0.02960 -0.0425 1.0000 0.2288
-2.000 -0.1049 0.03595 0.02718 -0.0438 1.0000 0.1967
-1.750 -0.0763 0.03452 0.02530 -0.0444 1.0000 0.1786
-1.500 -0.0492 0.03361 0.02391 -0.0447 1.0000 0.1660
-1.250 -0.0246 0.03270 0.02271 -0.0449 1.0000 0.1586
-1.000 -0.0012 0.03233 0.02196 -0.0449 1.0000 0.1553
-0.750 0.0204 0.03208 0.02148 -0.0448 1.0000 0.1546
-0.500 0.0596 0.03167 0.02083 -0.0477 0.9946 0.1529
-0.250 0.1182 0.03098 0.01992 -0.0533 0.9808 0.1519
0.000 0.1748 0.03057 0.01928 -0.0585 0.9656 0.1535
0.250 0.2291 0.03002 0.01876 -0.0637 0.9496 0.1631
0.500 0.2826 0.02959 0.01833 -0.0688 0.9326 0.1806
0.750 0.3369 0.02867 0.01797 -0.0740 0.9162 0.2559
1.000 0.3805 0.02689 0.01764 -0.0754 0.8994 1.0000
1.250 0.4347 0.02692 0.01720 -0.0796 0.8823 1.0000
1.500 0.4742 0.02710 0.01712 -0.0816 0.8621 1.0000
1.750 0.5173 0.02706 0.01689 -0.0837 0.8434 1.0000
2.000 0.5607 0.02689 0.01657 -0.0856 0.8259 1.0000
2.250 0.6022 0.02665 0.01622 -0.0869 0.8087 1.0000
2.500 0.6328 0.02681 0.01630 -0.0867 0.7888 1.0000
2.750 0.6651 0.02688 0.01630 -0.0866 0.7699 1.0000
3.000 0.6976 0.02692 0.01626 -0.0863 0.7519 1.0000
3.250 0.7290 0.02702 0.01631 -0.0857 0.7344 1.0000
3.500 0.7558 0.02745 0.01669 -0.0849 0.7160 1.0000
3.750 0.7797 0.02812 0.01735 -0.0839 0.6966 1.0000
4.000 0.8050 0.02873 0.01797 -0.0830 0.6789 1.0000
4.250 0.8302 0.02938 0.01861 -0.0821 0.6621 1.0000
4.500 0.8550 0.03008 0.01933 -0.0812 0.6459 1.0000
4.750 0.8790 0.03088 0.02015 -0.0804 0.6304 1.0000
5.000 0.9024 0.03176 0.02110 -0.0796 0.6155 1.0000
5.250 0.9250 0.03275 0.02217 -0.0789 0.6011 1.0000
5.500 0.9471 0.03383 0.02333 -0.0781 0.5873 1.0000
5.750 0.9688 0.03496 0.02456 -0.0773 0.5741 1.0000
6.000 0.9914 0.03605 0.02578 -0.0766 0.5618 1.0000
6.250 1.0178 0.03674 0.02653 -0.0759 0.5504 1.0000
6.500 1.0391 0.03791 0.02783 -0.0750 0.5377 1.0000
6.750 1.0566 0.03941 0.02950 -0.0740 0.5242 1.0000
7.000 1.0762 0.04054 0.03080 -0.0727 0.5101 1.0000
7.250 1.0971 0.04143 0.03183 -0.0714 0.4955 1.0000
7.500 1.1184 0.04226 0.03279 -0.0700 0.4807 1.0000
7.750 1.1389 0.04318 0.03387 -0.0686 0.4660 1.0000
8.000 1.1601 0.04400 0.03487 -0.0672 0.4509 1.0000
8.250 1.1833 0.04454 0.03554 -0.0657 0.4351 1.0000
8.500 1.2144 0.04414 0.03519 -0.0644 0.4176 1.0000
8.750 1.2306 0.04519 0.03646 -0.0624 0.3993 1.0000
9.000 1.2457 0.04624 0.03772 -0.0603 0.3798 1.0000
9.250 1.2786 0.04558 0.03704 -0.0590 0.3587 1.0000
9.500 1.2918 0.04699 0.03864 -0.0568 0.3391 1.0000
9.750 1.3066 0.04816 0.03998 -0.0546 0.3188 1.0000
10.000 1.3367 0.04813 0.03991 -0.0533 0.2975 1.0000
10.250 1.3406 0.04998 0.04204 -0.0504 0.2785 1.0000
10.500 1.3627 0.04834 0.04026 -0.0480 0.2499 1.0000
10.750 1.3736 0.04709 0.03885 -0.0448 0.2220 1.0000
11.000 1.3787 0.04695 0.03855 -0.0414 0.1965 1.0000
11.250 1.3706 0.04870 0.04044 -0.0372 0.1758 1.0000
11.500 1.3642 0.05041 0.04195 -0.0332 0.1540 1.0000
11.750 1.3538 0.05320 0.04473 -0.0292 0.1379 1.0000
12.000 1.3486 0.05635 0.04785 -0.0262 0.1244 1.0000
12.250 1.3479 0.05966 0.05113 -0.0240 0.1138 1.0000
12.500 1.3576 0.06298 0.05432 -0.0226 0.1037 1.0000
12.750 1.3398 0.06719 0.05898 -0.0204 0.1019 1.0000
13.000 1.3217 0.07192 0.06407 -0.0192 0.1003 1.0000
13.250 1.3011 0.07721 0.06969 -0.0190 0.0995 1.0000
13.500 1.2762 0.08335 0.07612 -0.0200 0.0995 1.0000
13.750 1.2470 0.09060 0.08363 -0.0224 0.1003 1.0000
14.000 1.2156 0.09897 0.09220 -0.0262 0.1017 1.0000
14.250 1.1853 0.10816 0.10153 -0.0307 0.1031 1.0000
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Polar data table (+)
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