GOE 795 smoothed (goe795sm-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 795 smoothed (goe795sm-il) Reynolds number: 50,000 Max Cl/Cd: 37.72 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe795sm-il-50000.txt Download as CSV file: xf-goe795sm-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 smoothed
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4521 0.11458 0.10745 -0.0186 1.0000 0.1990
-9.000 -0.4348 0.10939 0.10224 -0.0172 1.0000 0.2067
-8.750 -0.4517 0.10868 0.10169 -0.0188 1.0000 0.2134
-8.500 -0.4343 0.10369 0.09669 -0.0173 1.0000 0.2245
-8.250 -0.4329 0.10053 0.09361 -0.0170 1.0000 0.2329
-8.000 -0.4488 0.09948 0.09269 -0.0174 1.0000 0.2418
-7.750 -0.4431 0.09605 0.08932 -0.0160 1.0000 0.2554
-7.500 -0.4392 0.09278 0.08607 -0.0147 1.0000 0.2688
-7.250 -0.4362 0.08962 0.08298 -0.0132 1.0000 0.2817
-7.000 -0.4359 0.08663 0.08008 -0.0117 1.0000 0.2939
-6.750 -0.4394 0.08397 0.07752 -0.0099 1.0000 0.3062
-6.500 -0.4411 0.08121 0.07486 -0.0082 1.0000 0.3210
-6.250 -0.4437 0.07860 0.07234 -0.0065 1.0000 0.3380
-6.000 -0.4605 0.07697 0.07086 -0.0054 1.0000 0.3570
-5.750 -0.4429 0.07297 0.06687 -0.0016 1.0000 0.3781
-5.500 -0.4440 0.07061 0.06460 0.0023 1.0000 0.4107
-4.750 -0.4198 0.04814 0.04044 -0.0323 1.0000 0.1575
-4.500 -0.4053 0.04451 0.03668 -0.0311 1.0000 0.1558
-4.250 -0.3895 0.04097 0.03284 -0.0302 1.0000 0.1525
-4.000 -0.3700 0.03685 0.02772 -0.0295 1.0000 0.1435
-3.750 -0.3507 0.03393 0.02433 -0.0282 1.0000 0.1432
-3.500 -0.3324 0.03197 0.02232 -0.0269 1.0000 0.1526
-3.250 -0.3107 0.02976 0.01949 -0.0256 1.0000 0.1583
-3.000 -0.2888 0.02791 0.01748 -0.0243 1.0000 0.1655
-2.750 -0.2674 0.02658 0.01589 -0.0231 1.0000 0.1807
-2.500 -0.2438 0.02527 0.01434 -0.0220 1.0000 0.1963
-2.250 -0.2191 0.02408 0.01308 -0.0212 1.0000 0.2185
-2.000 -0.1938 0.02304 0.01201 -0.0205 1.0000 0.2530
-1.750 -0.1078 0.01780 0.00972 -0.0288 1.0000 1.0000
-1.500 -0.0888 0.01798 0.00925 -0.0275 1.0000 1.0000
-1.250 -0.0712 0.01819 0.00905 -0.0261 1.0000 1.0000
-1.000 -0.0537 0.01843 0.00895 -0.0247 1.0000 1.0000
-0.750 -0.0363 0.01870 0.00895 -0.0234 1.0000 1.0000
-0.500 -0.0189 0.01901 0.00898 -0.0222 1.0000 1.0000
-0.250 -0.0015 0.01934 0.00910 -0.0211 1.0000 1.0000
0.000 0.0159 0.01972 0.00929 -0.0200 1.0000 1.0000
0.250 0.0333 0.02012 0.00953 -0.0190 1.0000 1.0000
0.500 0.0506 0.02057 0.00983 -0.0181 1.0000 1.0000
0.750 0.0677 0.02105 0.01017 -0.0172 1.0000 1.0000
1.000 0.0848 0.02157 0.01059 -0.0165 1.0000 1.0000
1.250 0.1017 0.02214 0.01107 -0.0157 1.0000 1.0000
1.500 0.1183 0.02276 0.01162 -0.0151 1.0000 1.0000
1.750 0.1348 0.02342 0.01223 -0.0145 1.0000 1.0000
2.000 0.1510 0.02414 0.01290 -0.0139 1.0000 1.0000
2.250 0.1741 0.02505 0.01379 -0.0150 0.9968 1.0000
2.500 0.2298 0.02651 0.01528 -0.0221 0.9780 1.0000
2.750 0.2832 0.02778 0.01661 -0.0285 0.9589 1.0000
3.000 0.3311 0.02881 0.01772 -0.0336 0.9388 1.0000
3.250 0.3809 0.02973 0.01880 -0.0386 0.9182 1.0000
3.500 0.4258 0.03048 0.01969 -0.0425 0.8967 1.0000
3.750 0.4768 0.03109 0.02049 -0.0470 0.8752 1.0000
4.000 0.5178 0.03158 0.02122 -0.0495 0.8516 1.0000
4.250 0.5697 0.03175 0.02165 -0.0531 0.8283 1.0000
4.500 0.6321 0.03127 0.02153 -0.0575 0.8039 1.0000
4.750 0.6928 0.03022 0.02092 -0.0606 0.7761 1.0000
5.000 0.7458 0.02881 0.01988 -0.0612 0.7442 1.0000
5.250 0.7944 0.02717 0.01858 -0.0606 0.7084 1.0000
5.500 0.8345 0.02574 0.01744 -0.0586 0.6673 1.0000
5.750 0.8679 0.02456 0.01637 -0.0556 0.6185 1.0000
6.000 0.8893 0.02403 0.01581 -0.0514 0.5582 1.0000
6.250 0.9049 0.02399 0.01546 -0.0465 0.4818 1.0000
6.500 0.9128 0.02493 0.01579 -0.0413 0.3922 1.0000
6.750 0.9192 0.02662 0.01686 -0.0368 0.3084 1.0000
7.000 0.9281 0.02861 0.01824 -0.0332 0.2413 1.0000
7.250 0.9418 0.03088 0.02019 -0.0306 0.1893 1.0000
7.500 0.9637 0.03367 0.02279 -0.0291 0.1535 1.0000
7.750 0.9879 0.03661 0.02555 -0.0282 0.1306 1.0000
8.000 1.0123 0.03986 0.02894 -0.0273 0.1177 1.0000
8.250 1.0282 0.04247 0.03197 -0.0252 0.1077 1.0000
8.500 1.0451 0.04628 0.03612 -0.0235 0.1032 1.0000
8.750 1.0538 0.05006 0.04059 -0.0207 0.1015 1.0000
9.000 1.0579 0.05395 0.04501 -0.0178 0.1000 1.0000
9.250 1.0578 0.05784 0.04936 -0.0150 0.0988 1.0000
9.500 1.0541 0.06168 0.05357 -0.0121 0.0972 1.0000
9.750 1.0455 0.06578 0.05802 -0.0094 0.0970 1.0000
10.000 1.0283 0.07025 0.06283 -0.0067 0.0987 1.0000
10.250 1.0074 0.07446 0.06726 -0.0041 0.0995 1.0000
10.500 0.9855 0.07875 0.07168 -0.0022 0.1011 1.0000
10.750 0.9653 0.08355 0.07657 -0.0017 0.1025 1.0000
11.000 0.9515 0.08882 0.08189 -0.0021 0.1038 1.0000
11.250 0.9463 0.09437 0.08746 -0.0028 0.1048 1.0000
11.500 0.8922 0.10610 0.09922 -0.0114 0.1186 1.0000
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Polar data table (+)
Polar graphs
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