GOE 308 (MVA H.40) AIRFOIL (goe308-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 308 (MVA H.40) AIRFOIL (goe308-il) Reynolds number: 100,000 Max Cl/Cd: 54.26 at α=8.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe308-il-100000.txt Download as CSV file: xf-goe308-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 308 (MVA H.40) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3234 0.09281 0.08841 -0.0236 1.0000 0.0740
-7.000 -0.3323 0.09115 0.08685 -0.0218 1.0000 0.0759
-6.750 -0.3410 0.08966 0.08544 -0.0209 1.0000 0.0782
-6.500 -0.3519 0.08897 0.08481 -0.0213 1.0000 0.0799
-6.250 -0.3608 0.08937 0.08519 -0.0247 1.0000 0.0808
-6.000 -0.3632 0.08597 0.08184 -0.0238 1.0000 0.0816
-5.750 -0.3636 0.08154 0.07752 -0.0177 1.0000 0.0834
-5.500 -0.3641 0.07916 0.07519 -0.0156 1.0000 0.0854
-5.250 -0.3636 0.07699 0.07303 -0.0147 1.0000 0.0878
-5.000 -0.3599 0.07491 0.07093 -0.0154 1.0000 0.0914
-4.750 -0.3378 0.07317 0.06893 -0.0231 0.9984 0.0949
-4.500 -0.3165 0.06758 0.06341 -0.0235 0.9925 0.0973
-4.250 -0.2784 0.06369 0.05942 -0.0292 0.9846 0.1040
-4.000 -0.2387 0.05950 0.05502 -0.0360 0.9751 0.1108
-3.750 -0.2009 0.05619 0.05157 -0.0407 0.9664 0.1188
-3.500 -0.1599 0.05216 0.04731 -0.0463 0.9581 0.1251
-3.250 -0.1178 0.04992 0.04468 -0.0512 0.9470 0.1372
-3.000 -0.0890 0.04610 0.04095 -0.0528 0.9388 0.1448
-2.750 -0.0483 0.04310 0.03773 -0.0567 0.9301 0.1564
-2.500 -0.0137 0.04064 0.03503 -0.0590 0.9189 0.1697
-2.250 0.0241 0.03813 0.03236 -0.0615 0.9098 0.1855
-2.000 0.0635 0.03577 0.02985 -0.0643 0.9013 0.2134
-1.750 0.0959 0.03362 0.02758 -0.0655 0.8900 0.2421
-1.500 0.1601 0.03059 0.02374 -0.0706 0.8853 0.1829
-1.250 0.2057 0.02562 0.01758 -0.0706 0.8753 0.1026
-1.000 0.2533 0.02374 0.01524 -0.0732 0.8676 0.1062
-0.750 0.2972 0.02206 0.01317 -0.0751 0.8573 0.1080
-0.500 0.3362 0.02051 0.01161 -0.0766 0.8445 0.1141
-0.250 0.3762 0.01920 0.01020 -0.0779 0.8308 0.1260
0.000 0.4137 0.01818 0.00925 -0.0789 0.8153 0.1614
0.250 0.4499 0.01740 0.00848 -0.0797 0.7984 0.2110
0.500 0.4859 0.01688 0.00796 -0.0806 0.7798 0.2446
0.750 0.5140 0.01654 0.00765 -0.0803 0.7577 0.2802
1.000 0.5424 0.01613 0.00728 -0.0798 0.7380 0.3150
1.250 0.6600 0.01444 0.00670 -0.0976 0.7112 1.0000
1.500 0.6851 0.01460 0.00659 -0.0965 0.6924 1.0000
1.750 0.7082 0.01484 0.00663 -0.0953 0.6739 1.0000
2.000 0.7314 0.01511 0.00672 -0.0941 0.6570 1.0000
2.250 0.7549 0.01540 0.00686 -0.0930 0.6419 1.0000
2.500 0.7784 0.01572 0.00705 -0.0920 0.6283 1.0000
2.750 0.8024 0.01605 0.00725 -0.0911 0.6158 1.0000
3.000 0.8257 0.01640 0.00749 -0.0901 0.6037 1.0000
3.250 0.8476 0.01678 0.00784 -0.0889 0.5918 1.0000
3.500 0.8698 0.01716 0.00819 -0.0877 0.5803 1.0000
3.750 0.8923 0.01750 0.00846 -0.0866 0.5684 1.0000
4.000 0.9151 0.01781 0.00868 -0.0854 0.5564 1.0000
4.250 0.9368 0.01813 0.00896 -0.0841 0.5445 1.0000
4.500 0.9574 0.01851 0.00940 -0.0826 0.5332 1.0000
4.750 0.9795 0.01891 0.00980 -0.0815 0.5235 1.0000
5.000 1.0031 0.01929 0.01014 -0.0806 0.5143 1.0000
5.250 1.0229 0.01974 0.01069 -0.0791 0.5041 1.0000
5.500 1.0451 0.02019 0.01118 -0.0780 0.4948 1.0000
5.750 1.0680 0.02059 0.01158 -0.0770 0.4850 1.0000
6.000 1.0871 0.02107 0.01218 -0.0753 0.4743 1.0000
6.250 1.1084 0.02155 0.01272 -0.0741 0.4642 1.0000
6.500 1.1324 0.02201 0.01319 -0.0733 0.4545 1.0000
6.750 1.1501 0.02254 0.01389 -0.0714 0.4431 1.0000
7.000 1.1689 0.02290 0.01430 -0.0696 0.4293 1.0000
7.250 1.1872 0.02291 0.01425 -0.0675 0.4115 1.0000
7.500 1.2040 0.02293 0.01426 -0.0652 0.3937 1.0000
7.750 1.2175 0.02304 0.01449 -0.0624 0.3769 1.0000
8.000 1.2299 0.02309 0.01467 -0.0594 0.3594 1.0000
8.250 1.2412 0.02309 0.01478 -0.0562 0.3409 1.0000
8.500 1.2511 0.02308 0.01483 -0.0528 0.3213 1.0000
8.750 1.2594 0.02321 0.01512 -0.0492 0.2973 1.0000
9.000 1.2636 0.02351 0.01539 -0.0450 0.2636 1.0000
9.250 1.2647 0.02432 0.01600 -0.0406 0.2158 1.0000
9.500 1.2581 0.02580 0.01708 -0.0354 0.1647 1.0000
9.750 1.2469 0.02777 0.01862 -0.0300 0.0967 1.0000
10.000 1.2336 0.03008 0.02056 -0.0250 0.0689 1.0000
10.250 1.2284 0.03202 0.02250 -0.0212 0.0614 1.0000
10.500 1.2235 0.03404 0.02460 -0.0180 0.0573 1.0000
11.000 1.2112 0.03872 0.02952 -0.0128 0.0522 1.0000
11.250 1.2056 0.04130 0.03226 -0.0109 0.0501 1.0000
11.500 1.1989 0.04417 0.03527 -0.0095 0.0484 1.0000
11.750 1.1917 0.04729 0.03851 -0.0085 0.0471 1.0000
12.000 1.1853 0.05047 0.04179 -0.0076 0.0462 1.0000
12.250 1.1817 0.05342 0.04483 -0.0068 0.0454 1.0000
12.500 1.1845 0.05564 0.04706 -0.0052 0.0446 1.0000
12.750 1.2014 0.05663 0.04799 -0.0027 0.0437 1.0000
13.000 1.2238 0.05766 0.04909 -0.0007 0.0431 1.0000
13.250 1.2385 0.05955 0.05115 0.0007 0.0417 1.0000
13.500 1.2523 0.06171 0.05348 0.0018 0.0406 1.0000
13.750 1.2659 0.06419 0.05616 0.0029 0.0400 1.0000
14.000 1.2758 0.06725 0.05950 0.0039 0.0402 1.0000
14.250 1.2776 0.07087 0.06340 0.0045 0.0404 1.0000
14.500 1.2740 0.07484 0.06764 0.0047 0.0409 1.0000
14.750 1.2650 0.07927 0.07234 0.0044 0.0412 1.0000
15.000 1.2532 0.08405 0.07738 0.0036 0.0416 1.0000
15.250 1.2384 0.08930 0.08287 0.0023 0.0420 1.0000
15.500 1.2227 0.09483 0.08861 0.0005 0.0424 1.0000
15.750 1.2044 0.10099 0.09498 -0.0019 0.0428 1.0000
16.000 1.1875 0.10722 0.10140 -0.0047 0.0432 1.0000
16.250 1.1693 0.11407 0.10841 -0.0080 0.0435 1.0000
16.500 1.1565 0.12071 0.11522 -0.0108 0.0441 1.0000
16.750 1.1332 0.12821 0.12290 -0.0162 0.0444 1.0000
17.000 1.1024 0.13819 0.13308 -0.0237 0.0449 1.0000
17.250 0.9910 0.17631 0.17127 -0.0495 0.0513 1.0000
17.500 0.9894 0.18272 0.17766 -0.0521 0.0530 1.0000
17.750 0.9970 0.18620 0.18118 -0.0527 0.0547 1.0000
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Polar data table (+)
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