GOE 309 (MVA H.41) AIRFOIL (goe309-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 309 (MVA H.41) AIRFOIL (goe309-il) Reynolds number: 100,000 Max Cl/Cd: 54.7 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe309-il-100000.txt Download as CSV file: xf-goe309-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 309 (MVA H.41) 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3441 0.09515 0.09071 -0.0210 1.0000 0.0676
-7.500 -0.3463 0.09297 0.08861 -0.0244 1.0000 0.0698
-7.250 -0.3473 0.09198 0.08767 -0.0315 1.0000 0.0711
-7.000 -0.3469 0.09123 0.08686 -0.0360 1.0000 0.0716
-6.750 -0.3396 0.08354 0.07935 -0.0294 1.0000 0.0735
-6.500 -0.3372 0.08063 0.07651 -0.0273 1.0000 0.0754
-6.250 -0.3395 0.07848 0.07442 -0.0258 1.0000 0.0773
-6.000 -0.3467 0.07685 0.07285 -0.0238 1.0000 0.0791
-5.750 -0.3560 0.07557 0.07161 -0.0218 1.0000 0.0810
-5.500 -0.3596 0.07543 0.07138 -0.0229 1.0000 0.0841
-5.250 -0.3469 0.07222 0.06803 -0.0262 0.9974 0.0856
-5.000 -0.3234 0.06656 0.06246 -0.0275 0.9916 0.0888
-4.750 -0.2695 0.06291 0.05837 -0.0386 0.9830 0.0996
-4.500 -0.2469 0.05791 0.05350 -0.0397 0.9752 0.1046
-4.250 -0.2012 0.05390 0.04913 -0.0469 0.9673 0.1148
-3.750 -0.1287 0.04665 0.04159 -0.0545 0.9506 0.1346
-3.500 -0.0833 0.04376 0.03832 -0.0597 0.9434 0.1570
-3.250 -0.0495 0.04067 0.03508 -0.0622 0.9340 0.1725
-3.000 -0.0095 0.03772 0.03202 -0.0654 0.9278 0.1943
-2.750 0.0182 0.03558 0.02978 -0.0664 0.9164 0.2322
-2.250 0.1169 0.02811 0.02040 -0.0703 0.8998 0.1115
-2.000 0.1481 0.02634 0.01823 -0.0704 0.8882 0.1117
-1.750 0.1794 0.02446 0.01610 -0.0704 0.8773 0.1092
-1.500 0.2118 0.02296 0.01427 -0.0702 0.8673 0.1087
-1.250 0.2425 0.02180 0.01280 -0.0697 0.8565 0.1107
-1.000 0.2695 0.02086 0.01176 -0.0690 0.8439 0.1176
-0.750 0.2967 0.02019 0.01093 -0.0681 0.8313 0.1258
-0.500 0.3232 0.01929 0.01006 -0.0672 0.8189 0.1355
-0.250 0.3490 0.01848 0.00926 -0.0659 0.8068 0.1558
0.000 0.3740 0.01771 0.00871 -0.0647 0.7950 0.2080
0.250 0.3986 0.01723 0.00841 -0.0635 0.7834 0.2847
0.500 0.4763 0.01531 0.00795 -0.0722 0.7703 1.0000
0.750 0.4995 0.01549 0.00791 -0.0710 0.7566 1.0000
1.000 0.5227 0.01569 0.00794 -0.0698 0.7433 1.0000
1.250 0.5460 0.01590 0.00799 -0.0687 0.7302 1.0000
1.500 0.5694 0.01612 0.00808 -0.0677 0.7177 1.0000
1.750 0.5930 0.01633 0.00817 -0.0666 0.7058 1.0000
2.000 0.6170 0.01650 0.00820 -0.0655 0.6947 1.0000
2.250 0.6405 0.01665 0.00824 -0.0644 0.6819 1.0000
2.500 0.6637 0.01674 0.00823 -0.0631 0.6677 1.0000
2.750 0.6870 0.01681 0.00820 -0.0618 0.6532 1.0000
3.000 0.7104 0.01691 0.00823 -0.0607 0.6394 1.0000
3.250 0.7341 0.01709 0.00836 -0.0598 0.6266 1.0000
3.500 0.7580 0.01729 0.00854 -0.0589 0.6146 1.0000
3.750 0.7821 0.01749 0.00873 -0.0581 0.6032 1.0000
4.000 0.8067 0.01766 0.00885 -0.0572 0.5922 1.0000
4.250 0.8314 0.01782 0.00897 -0.0564 0.5809 1.0000
4.500 0.8553 0.01807 0.00925 -0.0557 0.5685 1.0000
4.750 0.8794 0.01833 0.00956 -0.0549 0.5563 1.0000
5.000 0.9036 0.01857 0.00981 -0.0542 0.5436 1.0000
5.250 0.9278 0.01879 0.01006 -0.0534 0.5304 1.0000
5.500 0.9520 0.01903 0.01031 -0.0525 0.5165 1.0000
5.750 0.9759 0.01928 0.01062 -0.0517 0.5017 1.0000
6.000 0.9996 0.01953 0.01090 -0.0508 0.4857 1.0000
6.250 1.0218 0.01950 0.01078 -0.0494 0.4628 1.0000
6.500 1.0427 0.01948 0.01069 -0.0479 0.4371 1.0000
6.750 1.0639 0.01978 0.01111 -0.0468 0.4160 1.0000
7.000 1.0847 0.01999 0.01128 -0.0455 0.3935 1.0000
7.250 1.1030 0.02017 0.01148 -0.0439 0.3642 1.0000
7.500 1.1225 0.02052 0.01191 -0.0426 0.3390 1.0000
7.750 1.1416 0.02095 0.01237 -0.0413 0.3137 1.0000
8.000 1.1575 0.02152 0.01285 -0.0397 0.2791 1.0000
8.250 1.1740 0.02226 0.01351 -0.0382 0.2508 1.0000
8.500 1.1893 0.02313 0.01431 -0.0365 0.2222 1.0000
8.750 1.2041 0.02409 0.01522 -0.0348 0.1956 1.0000
9.000 1.2166 0.02525 0.01628 -0.0329 0.1580 1.0000
9.250 1.2122 0.02778 0.01804 -0.0296 0.0666 1.0000
9.500 1.2123 0.02987 0.01995 -0.0265 0.0488 1.0000
9.750 1.2149 0.03150 0.02165 -0.0235 0.0445 1.0000
10.000 1.2183 0.03316 0.02352 -0.0210 0.0424 1.0000
10.250 1.2200 0.03506 0.02559 -0.0187 0.0410 1.0000
10.500 1.2196 0.03724 0.02795 -0.0168 0.0400 1.0000
10.750 1.2174 0.03974 0.03064 -0.0152 0.0393 1.0000
11.000 1.2136 0.04256 0.03363 -0.0141 0.0387 1.0000
11.250 1.2091 0.04562 0.03684 -0.0133 0.0383 1.0000
11.500 1.2047 0.04878 0.04015 -0.0127 0.0380 1.0000
11.750 1.2018 0.05185 0.04333 -0.0120 0.0378 1.0000
12.000 1.2020 0.05455 0.04611 -0.0109 0.0375 1.0000
12.250 1.2086 0.05655 0.04808 -0.0089 0.0369 1.0000
12.500 1.2192 0.05837 0.05001 -0.0075 0.0363 1.0000
12.750 1.2315 0.06021 0.05201 -0.0059 0.0356 1.0000
13.000 1.2507 0.06181 0.05372 -0.0039 0.0354 1.0000
13.250 1.2730 0.06384 0.05592 -0.0018 0.0357 1.0000
13.500 1.2915 0.06681 0.05908 -0.0003 0.0362 1.0000
13.750 1.3119 0.07101 0.06349 0.0010 0.0369 1.0000
14.000 1.3072 0.07402 0.06679 0.0014 0.0374 1.0000
14.250 1.2959 0.07760 0.07067 0.0011 0.0379 1.0000
14.500 1.2799 0.08206 0.07546 0.0002 0.0384 1.0000
14.750 1.2615 0.08733 0.08105 -0.0013 0.0390 1.0000
15.000 1.2406 0.09333 0.08736 -0.0036 0.0396 1.0000
15.250 1.2159 0.10010 0.09441 -0.0070 0.0400 1.0000
15.500 1.1906 0.10762 0.10218 -0.0112 0.0403 1.0000
15.750 1.1645 0.11602 0.11081 -0.0165 0.0406 1.0000
16.000 1.1367 0.12559 0.12058 -0.0228 0.0408 1.0000
16.250 1.1059 0.13683 0.13201 -0.0306 0.0411 1.0000
16.500 1.0671 0.15183 0.14714 -0.0411 0.0415 1.0000
16.750 1.0239 0.17135 0.16661 -0.0533 0.0434 1.0000
17.000 1.0160 0.18013 0.17535 -0.0575 0.0452 1.0000
17.250 1.0194 0.18521 0.18045 -0.0593 0.0469 1.0000
17.500 1.0019 0.20191 0.19702 -0.0676 0.0558 1.0000
17.750 0.7390 0.17589 0.17137 -0.0372 0.0559 1.0000
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Polar data table (+)
Polar graphs
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