GOE 795 AIRFOIL (goe795-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 795 AIRFOIL (goe795-il) Reynolds number: 50,000 Max Cl/Cd: 37.78 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe795-il-50000-n5.txt Download as CSV file: xf-goe795-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3681 0.11131 0.10445 -0.0264 1.0000 0.1064
-9.750 -0.3651 0.10498 0.09806 -0.0282 1.0000 0.0722
-9.250 -0.4574 0.10360 0.09641 -0.0293 1.0000 0.0631
-9.000 -0.4504 0.09993 0.09275 -0.0287 1.0000 0.0610
-8.750 -0.4498 0.09628 0.08916 -0.0293 1.0000 0.0593
-8.500 -0.4520 0.09258 0.08553 -0.0303 1.0000 0.0577
-8.250 -0.4572 0.08882 0.08187 -0.0315 1.0000 0.0563
-8.000 -0.4660 0.08499 0.07815 -0.0329 1.0000 0.0550
-7.500 -0.4846 0.07345 0.06665 -0.0409 1.0000 0.0511
-7.250 -0.4839 0.06952 0.06271 -0.0412 1.0000 0.0507
-7.000 -0.4829 0.06550 0.05863 -0.0414 1.0000 0.0504
-6.750 -0.4812 0.06134 0.05438 -0.0415 1.0000 0.0502
-6.500 -0.4781 0.05724 0.05012 -0.0414 1.0000 0.0499
-6.250 -0.4742 0.05290 0.04551 -0.0412 1.0000 0.0502
-6.000 -0.4682 0.04864 0.04084 -0.0406 1.0000 0.0510
-5.750 -0.4593 0.04553 0.03754 -0.0395 1.0000 0.0526
-5.500 -0.4467 0.04377 0.03573 -0.0382 1.0000 0.0552
-5.250 -0.4343 0.04073 0.03227 -0.0370 1.0000 0.0565
-5.000 -0.4204 0.03762 0.02870 -0.0356 1.0000 0.0572
-4.750 -0.4046 0.03477 0.02537 -0.0342 1.0000 0.0583
-4.500 -0.3869 0.03219 0.02229 -0.0327 1.0000 0.0600
-4.250 -0.3673 0.02987 0.01943 -0.0313 1.0000 0.0624
-4.000 -0.3472 0.02804 0.01727 -0.0299 1.0000 0.0653
-3.750 -0.3276 0.02690 0.01600 -0.0286 1.0000 0.0716
-3.500 -0.3076 0.02592 0.01484 -0.0274 1.0000 0.0817
-3.250 -0.2880 0.02520 0.01399 -0.0262 1.0000 0.0968
-3.000 -0.2653 0.02413 0.01270 -0.0252 1.0000 0.1092
-2.750 -0.2415 0.02317 0.01159 -0.0244 1.0000 0.1234
-2.500 -0.2196 0.02257 0.01096 -0.0236 1.0000 0.1476
-2.250 -0.1977 0.02200 0.01038 -0.0227 1.0000 0.1738
-2.000 -0.1766 0.02152 0.00995 -0.0219 1.0000 0.2067
-1.750 -0.1546 0.02100 0.00962 -0.0215 0.9993 0.2653
-1.500 -0.1204 0.02006 0.00938 -0.0235 0.9930 0.3911
-1.250 -0.0576 0.01829 0.00915 -0.0295 0.9939 1.0000
-1.000 -0.0196 0.01859 0.00898 -0.0321 0.9850 1.0000
-0.750 0.0171 0.01888 0.00894 -0.0344 0.9762 1.0000
-0.500 0.0549 0.01920 0.00898 -0.0369 0.9679 1.0000
-0.250 0.0901 0.01946 0.00902 -0.0389 0.9584 1.0000
0.000 0.1243 0.01972 0.00908 -0.0407 0.9488 1.0000
0.250 0.1613 0.02000 0.00919 -0.0429 0.9401 1.0000
0.500 0.1966 0.02025 0.00933 -0.0447 0.9304 1.0000
0.750 0.2296 0.02048 0.00948 -0.0461 0.9198 1.0000
1.000 0.2648 0.02070 0.00962 -0.0478 0.9094 1.0000
1.250 0.3035 0.02083 0.00971 -0.0500 0.8983 1.0000
1.500 0.3442 0.02085 0.00973 -0.0523 0.8861 1.0000
1.750 0.3849 0.02081 0.00972 -0.0546 0.8734 1.0000
2.000 0.4205 0.02082 0.00976 -0.0558 0.8599 1.0000
2.250 0.4532 0.02086 0.00986 -0.0565 0.8466 1.0000
2.500 0.4849 0.02093 0.01003 -0.0569 0.8333 1.0000
2.750 0.5162 0.02100 0.01019 -0.0573 0.8199 1.0000
3.000 0.5474 0.02106 0.01035 -0.0575 0.8062 1.0000
3.250 0.5787 0.02110 0.01052 -0.0577 0.7919 1.0000
3.500 0.6104 0.02112 0.01072 -0.0578 0.7771 1.0000
3.750 0.6369 0.02124 0.01099 -0.0571 0.7593 1.0000
4.000 0.6660 0.02127 0.01117 -0.0566 0.7405 1.0000
4.250 0.6949 0.02119 0.01122 -0.0557 0.7169 1.0000
4.500 0.7213 0.02109 0.01123 -0.0542 0.6879 1.0000
4.750 0.7459 0.02105 0.01134 -0.0524 0.6556 1.0000
5.000 0.7676 0.02110 0.01148 -0.0503 0.6189 1.0000
5.250 0.7877 0.02118 0.01158 -0.0478 0.5744 1.0000
5.500 0.8059 0.02137 0.01168 -0.0450 0.5202 1.0000
5.750 0.8228 0.02178 0.01187 -0.0423 0.4595 1.0000
6.000 0.8378 0.02247 0.01230 -0.0395 0.3972 1.0000
6.250 0.8512 0.02340 0.01306 -0.0369 0.3386 1.0000
6.500 0.8641 0.02448 0.01397 -0.0345 0.2816 1.0000
6.750 0.8752 0.02576 0.01500 -0.0320 0.2187 1.0000
7.000 0.8854 0.02732 0.01620 -0.0296 0.1738 1.0000
7.250 0.8982 0.02895 0.01769 -0.0275 0.1469 1.0000
7.500 0.9131 0.03057 0.01928 -0.0256 0.1300 1.0000
7.750 0.9312 0.03216 0.02094 -0.0241 0.1166 1.0000
8.000 0.9481 0.03369 0.02251 -0.0226 0.1022 1.0000
8.250 0.9654 0.03538 0.02440 -0.0211 0.0889 1.0000
8.500 0.9790 0.03707 0.02624 -0.0193 0.0744 1.0000
8.750 0.9918 0.03902 0.02827 -0.0176 0.0623 1.0000
9.000 1.0047 0.04110 0.03046 -0.0159 0.0531 1.0000
9.250 1.0204 0.04381 0.03353 -0.0143 0.0458 1.0000
9.500 1.0349 0.04668 0.03655 -0.0130 0.0421 1.0000
9.750 1.0455 0.05030 0.04052 -0.0112 0.0394 1.0000
10.000 1.0480 0.05352 0.04426 -0.0087 0.0372 1.0000
10.250 1.0448 0.05657 0.04768 -0.0060 0.0350 1.0000
10.500 1.0393 0.05928 0.05064 -0.0033 0.0333 1.0000
10.750 1.0314 0.06226 0.05383 -0.0010 0.0321 1.0000
11.000 1.0216 0.06553 0.05730 0.0007 0.0314 1.0000
11.250 1.0095 0.06918 0.06115 0.0017 0.0310 1.0000
11.500 0.9941 0.07345 0.06563 0.0019 0.0308 1.0000
11.750 0.9750 0.07848 0.07090 0.0009 0.0309 1.0000
12.000 0.9507 0.08491 0.07757 -0.0018 0.0315 1.0000
12.250 0.9111 0.09578 0.08870 -0.0086 0.0341 1.0000
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Polar data table (+)
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