GOE 137 (MVA H.15) AIRFOIL (goe137-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 137 (MVA H.15) AIRFOIL (goe137-il) Reynolds number: 500,000 Max Cl/Cd: 97.27 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe137-il-500000-n5.txt Download as CSV file: xf-goe137-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 137 (MVA H.15) 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 -0.3658 0.09414 0.09201 -0.0208 1.0000 0.0073
-8.500 -0.3632 0.09013 0.08802 -0.0230 1.0000 0.0075
-8.000 -0.3619 0.08197 0.07993 -0.0275 0.9976 0.0078
-7.000 -0.3218 0.01721 0.01278 -0.0859 0.9272 0.0117
-6.750 -0.2963 0.01628 0.01166 -0.0857 0.9157 0.0126
-6.500 -0.2694 0.01667 0.01210 -0.0852 0.9029 0.0133
-6.250 -0.2429 0.01675 0.01213 -0.0848 0.8879 0.0142
-6.000 -0.2176 0.01564 0.01071 -0.0844 0.8710 0.0158
-5.750 -0.1921 0.01470 0.00946 -0.0840 0.8516 0.0170
-5.500 -0.1655 0.01486 0.00954 -0.0836 0.8288 0.0178
-5.250 -0.1389 0.01510 0.00969 -0.0832 0.8042 0.0187
-5.000 -0.1122 0.01501 0.00942 -0.0829 0.7802 0.0202
-4.750 -0.0853 0.01458 0.00875 -0.0827 0.7594 0.0218
-4.500 -0.0579 0.01438 0.00834 -0.0825 0.7410 0.0231
-4.250 -0.0302 0.01442 0.00822 -0.0824 0.7250 0.0238
-4.000 -0.0036 0.01306 0.00659 -0.0824 0.7111 0.0254
-3.750 0.0239 0.01277 0.00620 -0.0824 0.6980 0.0267
-3.500 0.0516 0.01247 0.00578 -0.0823 0.6859 0.0278
-3.000 0.1073 0.01177 0.00483 -0.0823 0.6644 0.0300
-2.750 0.1353 0.01145 0.00442 -0.0822 0.6552 0.0311
-2.500 0.1632 0.01114 0.00399 -0.0822 0.6462 0.0318
-2.250 0.1913 0.01085 0.00362 -0.0822 0.6377 0.0323
-2.000 0.2192 0.01062 0.00330 -0.0821 0.6282 0.0327
-1.750 0.2471 0.01041 0.00301 -0.0821 0.6163 0.0331
-1.500 0.2751 0.01023 0.00275 -0.0821 0.6042 0.0334
-1.250 0.3032 0.01010 0.00256 -0.0821 0.5943 0.0338
-1.000 0.3313 0.00999 0.00239 -0.0821 0.5858 0.0342
-0.750 0.3595 0.00984 0.00220 -0.0821 0.5766 0.0343
-0.500 0.3877 0.00970 0.00200 -0.0822 0.5672 0.0348
-0.250 0.4158 0.00960 0.00182 -0.0822 0.5574 0.0357
0.000 0.4441 0.00952 0.00169 -0.0822 0.5480 0.0377
0.250 0.4722 0.00948 0.00160 -0.0822 0.5377 0.0413
0.500 0.5002 0.00947 0.00155 -0.0822 0.5254 0.0467
0.750 0.5280 0.00935 0.00156 -0.0823 0.5112 0.1090
1.000 0.5557 0.00936 0.00159 -0.0823 0.4948 0.1402
1.500 0.6110 0.00926 0.00170 -0.0825 0.4679 0.2602
2.000 0.6629 0.00779 0.00189 -0.0820 0.4441 1.0000
2.250 0.6905 0.00794 0.00196 -0.0820 0.4319 1.0000
2.500 0.7179 0.00810 0.00205 -0.0819 0.4200 1.0000
2.750 0.7453 0.00827 0.00215 -0.0819 0.4087 1.0000
3.000 0.7727 0.00844 0.00225 -0.0818 0.3968 1.0000
3.250 0.8000 0.00860 0.00238 -0.0818 0.3860 1.0000
3.500 0.8273 0.00877 0.00250 -0.0818 0.3766 1.0000
4.000 0.8817 0.00913 0.00280 -0.0817 0.3559 1.0000
4.250 0.9085 0.00934 0.00296 -0.0816 0.3421 1.0000
4.500 0.9348 0.00962 0.00315 -0.0814 0.3234 1.0000
4.750 0.9611 0.00990 0.00335 -0.0813 0.3063 1.0000
5.000 0.9868 0.01023 0.00360 -0.0811 0.2805 1.0000
5.250 1.0112 0.01074 0.00390 -0.0807 0.2396 1.0000
5.500 1.0340 0.01145 0.00434 -0.0802 0.1899 1.0000
5.750 1.0584 0.01193 0.00473 -0.0799 0.1720 1.0000
6.000 1.0834 0.01232 0.00508 -0.0796 0.1604 1.0000
6.250 1.1083 0.01270 0.00543 -0.0793 0.1503 1.0000
6.500 1.1329 0.01310 0.00579 -0.0789 0.1360 1.0000
6.750 1.1515 0.01422 0.00652 -0.0779 0.0702 1.0000
7.000 1.1686 0.01549 0.00749 -0.0766 0.0186 1.0000
7.250 1.1915 0.01602 0.00806 -0.0760 0.0145 1.0000
7.500 1.2139 0.01660 0.00871 -0.0752 0.0115 1.0000
7.750 1.2368 0.01708 0.00926 -0.0746 0.0107 1.0000
8.000 1.2589 0.01762 0.00990 -0.0738 0.0099 1.0000
8.250 1.2800 0.01822 0.01059 -0.0730 0.0090 1.0000
8.500 1.2997 0.01894 0.01138 -0.0720 0.0082 1.0000
8.750 1.3174 0.01982 0.01235 -0.0706 0.0075 1.0000
9.000 1.3363 0.02053 0.01314 -0.0695 0.0071 1.0000
9.250 1.3534 0.02134 0.01403 -0.0682 0.0067 1.0000
9.500 1.3690 0.02221 0.01499 -0.0666 0.0064 1.0000
9.750 1.3828 0.02315 0.01604 -0.0649 0.0061 1.0000
10.000 1.3930 0.02412 0.01709 -0.0626 0.0058 1.0000
10.250 1.4010 0.02521 0.01826 -0.0601 0.0056 1.0000
10.500 1.4065 0.02655 0.01968 -0.0576 0.0054 1.0000
10.750 1.4050 0.02851 0.02176 -0.0548 0.0052 1.0000
11.000 1.4117 0.02998 0.02333 -0.0531 0.0050 1.0000
11.250 1.4180 0.03158 0.02504 -0.0516 0.0048 1.0000
11.500 1.4225 0.03345 0.02702 -0.0503 0.0046 1.0000
11.750 1.4245 0.03570 0.02939 -0.0492 0.0045 1.0000
12.000 1.4256 0.03819 0.03201 -0.0484 0.0044 1.0000
12.250 1.4260 0.04090 0.03484 -0.0479 0.0043 1.0000
12.500 1.4257 0.04377 0.03785 -0.0475 0.0042 1.0000
12.750 1.4245 0.04686 0.04105 -0.0473 0.0041 1.0000
13.000 1.4229 0.05006 0.04437 -0.0473 0.0040 1.0000
13.250 1.4205 0.05340 0.04782 -0.0474 0.0039 1.0000
13.500 1.4173 0.05690 0.05144 -0.0476 0.0038 1.0000
13.750 1.4135 0.06053 0.05518 -0.0479 0.0038 1.0000
14.000 1.4090 0.06432 0.05907 -0.0484 0.0037 1.0000
14.250 1.4040 0.06829 0.06315 -0.0490 0.0037 1.0000
14.500 1.3983 0.07244 0.06740 -0.0498 0.0036 1.0000
14.750 1.3922 0.07674 0.07182 -0.0507 0.0036 1.0000
15.000 1.3855 0.08125 0.07643 -0.0517 0.0035 1.0000
15.250 1.3783 0.08589 0.08118 -0.0528 0.0035 1.0000
15.500 1.3702 0.09071 0.08611 -0.0540 0.0034 1.0000
15.750 1.3612 0.09571 0.09123 -0.0553 0.0034 1.0000
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Polar data table (+)
Polar graphs
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