GOE 741 AIRFOIL (goe741-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 741 AIRFOIL (goe741-il) Reynolds number: 50,000 Max Cl/Cd: 14.06 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe741-il-50000-n5.txt Download as CSV file: xf-goe741-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 741 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2664 0.12320 0.11618 -0.0133 0.7312 0.1402
-10.000 -0.2742 0.12109 0.11407 -0.0160 0.7266 0.1414
-9.750 -0.2760 0.11825 0.11125 -0.0189 0.7208 0.1418
-9.250 -0.2713 0.10381 0.09667 -0.0264 0.7117 0.0902
-9.000 -0.2571 0.10101 0.09381 -0.0258 0.7066 0.0887
-8.750 -0.2493 0.09757 0.09040 -0.0276 0.7005 0.0870
-8.500 -0.2476 0.09380 0.08665 -0.0298 0.6952 0.0852
-8.000 -0.2815 0.08281 0.07560 -0.0391 0.6882 0.0806
-7.750 -0.2844 0.07942 0.07220 -0.0405 0.6832 0.0804
-7.500 -0.2881 0.07555 0.06826 -0.0422 0.6782 0.0804
-7.250 -0.2904 0.07179 0.06439 -0.0432 0.6738 0.0804
-7.000 -0.2923 0.06799 0.06042 -0.0435 0.6702 0.0804
-6.750 -0.2910 0.06437 0.05660 -0.0437 0.6664 0.0804
-6.500 -0.2862 0.06087 0.05291 -0.0441 0.6611 0.0803
-6.250 -0.2810 0.05750 0.04927 -0.0437 0.6564 0.0802
-6.000 -0.2754 0.05418 0.04558 -0.0426 0.6525 0.0804
-5.750 -0.2682 0.05100 0.04195 -0.0411 0.6492 0.0806
-5.500 -0.2505 0.04947 0.04035 -0.0409 0.6436 0.0817
-5.250 -0.2329 0.04813 0.03888 -0.0404 0.6385 0.0833
-5.000 -0.2169 0.04642 0.03690 -0.0392 0.6344 0.0854
-4.750 -0.2013 0.04436 0.03441 -0.0377 0.6311 0.0875
-4.500 -0.1838 0.04237 0.03193 -0.0367 0.6266 0.0893
-4.250 -0.1634 0.04091 0.03016 -0.0362 0.6211 0.0910
-4.000 -0.1415 0.04002 0.02918 -0.0356 0.6167 0.0933
-3.750 -0.1190 0.03906 0.02800 -0.0347 0.6132 0.0969
-3.500 -0.0950 0.03778 0.02626 -0.0336 0.6104 0.1017
-3.250 -0.0718 0.03755 0.02613 -0.0340 0.6041 0.1055
-3.000 -0.0466 0.03693 0.02532 -0.0339 0.5992 0.1111
-2.750 -0.0206 0.03632 0.02462 -0.0335 0.5955 0.1178
-2.500 0.0078 0.03565 0.02372 -0.0331 0.5925 0.1274
-2.250 0.0334 0.03572 0.02392 -0.0336 0.5876 0.1366
-2.000 0.0599 0.03586 0.02409 -0.0342 0.5819 0.1489
-1.750 0.0885 0.03577 0.02395 -0.0344 0.5778 0.1647
-1.500 0.1177 0.03558 0.02367 -0.0344 0.5746 0.1845
-1.250 0.1477 0.03529 0.02330 -0.0343 0.5720 0.2073
-1.000 0.1672 0.03627 0.02441 -0.0352 0.5647 0.2270
-0.750 0.1910 0.03637 0.02460 -0.0351 0.5600 0.2517
-0.500 0.2167 0.03617 0.02443 -0.0346 0.5566 0.2818
-0.250 0.2422 0.03577 0.02414 -0.0338 0.5539 0.3154
0.000 0.2547 0.03679 0.02537 -0.0335 0.5473 0.3476
0.250 0.2684 0.03709 0.02605 -0.0325 0.5416 0.4033
0.750 0.4831 0.03576 0.02555 -0.0575 0.5349 1.0000
1.000 0.4936 0.03751 0.02726 -0.0571 0.5280 1.0000
1.250 0.5061 0.03878 0.02843 -0.0561 0.5218 1.0000
1.500 0.5257 0.03917 0.02866 -0.0546 0.5181 1.0000
1.750 0.5482 0.03928 0.02860 -0.0531 0.5154 1.0000
2.000 0.5428 0.04216 0.03153 -0.0520 0.5058 1.0000
2.250 0.5567 0.04300 0.03227 -0.0504 0.5006 1.0000
2.500 0.5788 0.04312 0.03224 -0.0489 0.4975 1.0000
2.750 0.6042 0.04296 0.03192 -0.0474 0.4952 1.0000
3.000 0.5771 0.04720 0.03626 -0.0452 0.4820 1.0000
3.250 0.5993 0.04726 0.03621 -0.0436 0.4788 1.0000
3.500 0.6264 0.04694 0.03575 -0.0421 0.4767 1.0000
4.000 0.6126 0.05170 0.04048 -0.0380 0.4598 1.0000
4.250 0.6399 0.05140 0.04006 -0.0365 0.4577 1.0000
4.750 0.6162 0.05614 0.04474 -0.0312 0.4412 1.0000
5.250 0.6011 0.06059 0.04911 -0.0268 0.4256 1.0000
5.500 0.6277 0.06050 0.04895 -0.0256 0.4232 1.0000
6.000 0.6162 0.06540 0.05379 -0.0225 0.4081 1.0000
6.250 0.6384 0.06572 0.05405 -0.0213 0.4055 1.0000
6.500 0.6133 0.07001 0.05835 -0.0202 0.3943 1.0000
6.750 0.6339 0.07046 0.05875 -0.0190 0.3911 1.0000
7.250 0.6278 0.07591 0.06418 -0.0174 0.3779 1.0000
7.500 0.6460 0.07673 0.06497 -0.0165 0.3750 1.0000
8.000 0.6412 0.08241 0.07066 -0.0155 0.3625 1.0000
8.250 0.6588 0.08331 0.07153 -0.0146 0.3594 1.0000
8.500 0.6808 0.08381 0.07201 -0.0137 0.3572 1.0000
8.750 0.6521 0.08979 0.07805 -0.0143 0.3488 1.0000
9.000 0.6636 0.09147 0.07972 -0.0138 0.3451 1.0000
9.250 0.6828 0.09232 0.08056 -0.0130 0.3426 1.0000
9.500 0.6700 0.09664 0.08492 -0.0134 0.3361 1.0000
9.750 0.6722 0.09950 0.08780 -0.0134 0.3318 1.0000
10.000 0.6853 0.10113 0.08945 -0.0129 0.3287 1.0000
10.250 0.7053 0.10196 0.09028 -0.0122 0.3263 1.0000
10.500 0.6876 0.10700 0.09537 -0.0131 0.3195 1.0000
10.750 0.6941 0.10934 0.09774 -0.0130 0.3152 1.0000
11.000 0.7107 0.11057 0.09898 -0.0125 0.3121 1.0000
11.250 0.7151 0.11312 0.10157 -0.0125 0.3076 1.0000
11.500 0.7097 0.11671 0.10521 -0.0131 0.3011 1.0000
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Polar data table (+)
Polar graphs
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