GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il) Reynolds number: 100,000 Max Cl/Cd: 63.07 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe233-il-100000-n5.txt Download as CSV file: xf-goe233-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 233 (MVA CA4) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.1359 0.10890 0.10386 -0.0730 0.9629 0.0738
-8.250 -0.0886 0.08846 0.08330 -0.0865 0.9374 0.0496
-8.000 -0.0753 0.08533 0.08016 -0.0886 0.9295 0.0490
-7.750 -0.0645 0.08196 0.07678 -0.0910 0.9214 0.0485
-7.500 -0.0566 0.07851 0.07332 -0.0933 0.9120 0.0482
-7.250 -0.0493 0.07452 0.06933 -0.0968 0.9027 0.0486
-7.000 -0.0389 0.06961 0.06439 -0.1022 0.8943 0.0490
-6.750 -0.0290 0.06471 0.05948 -0.1074 0.8846 0.0488
-6.500 0.0457 0.03400 0.02762 -0.1698 0.8759 0.0474
-6.250 0.1021 0.02943 0.02243 -0.1830 0.8698 0.0492
-6.000 0.1404 0.02765 0.02043 -0.1871 0.8641 0.0505
-5.750 0.1752 0.02659 0.01926 -0.1891 0.8599 0.0515
-5.500 0.2055 0.02585 0.01843 -0.1901 0.8530 0.0525
-5.250 0.2369 0.02522 0.01770 -0.1910 0.8468 0.0538
-5.000 0.2708 0.02462 0.01695 -0.1921 0.8425 0.0554
-4.750 0.3013 0.02414 0.01641 -0.1932 0.8347 0.0576
-4.500 0.3368 0.02343 0.01562 -0.1954 0.8290 0.0614
-4.250 0.3735 0.02272 0.01477 -0.1976 0.8245 0.0657
-4.000 0.4073 0.02206 0.01403 -0.1998 0.8164 0.0718
-3.750 0.4469 0.02104 0.01288 -0.2031 0.8110 0.0844
-3.500 0.4874 0.01985 0.01179 -0.2071 0.8054 0.1204
-3.250 0.5208 0.01931 0.01123 -0.2090 0.7977 0.1676
-3.000 0.5516 0.01922 0.01122 -0.2093 0.7921 0.1983
-2.750 0.5781 0.01947 0.01152 -0.2088 0.7839 0.2209
-2.500 0.6064 0.01960 0.01157 -0.2084 0.7770 0.2376
-2.250 0.6347 0.01976 0.01163 -0.2082 0.7704 0.2546
-2.000 0.6619 0.01997 0.01176 -0.2078 0.7627 0.2680
-1.750 0.6903 0.02024 0.01193 -0.2073 0.7571 0.2825
-1.500 0.7155 0.02070 0.01236 -0.2065 0.7493 0.2964
-1.250 0.7436 0.02096 0.01251 -0.2062 0.7430 0.3099
-1.000 0.7693 0.02130 0.01285 -0.2051 0.7373 0.3170
-0.750 0.7982 0.02129 0.01273 -0.2055 0.7299 0.3264
-0.250 0.8562 0.02129 0.01251 -0.2058 0.7178 0.3409
0.250 0.9117 0.02139 0.01254 -0.2052 0.7062 0.3509
0.500 0.9398 0.02143 0.01251 -0.2055 0.6991 0.3575
0.750 0.9667 0.02151 0.01260 -0.2051 0.6930 0.3618
1.000 0.9960 0.02153 0.01252 -0.2052 0.6876 0.3698
1.250 1.0215 0.02171 0.01275 -0.2048 0.6803 0.3754
1.500 1.0495 0.02175 0.01276 -0.2046 0.6745 0.3812
1.750 1.0780 0.02177 0.01270 -0.2049 0.6673 0.3865
2.000 1.1054 0.02176 0.01267 -0.2047 0.6594 0.3893
2.250 1.1327 0.02178 0.01268 -0.2044 0.6520 0.3923
2.500 1.1591 0.02185 0.01275 -0.2041 0.6435 0.3958
2.750 1.1880 0.02184 0.01267 -0.2041 0.6368 0.3992
3.000 1.2141 0.02200 0.01283 -0.2039 0.6282 0.4023
3.250 1.2423 0.02198 0.01278 -0.2037 0.6213 0.4049
3.500 1.2663 0.02219 0.01309 -0.2031 0.6119 0.4077
3.750 1.2940 0.02224 0.01311 -0.2028 0.6046 0.4110
4.000 1.3184 0.02247 0.01340 -0.2023 0.5954 0.4142
4.250 1.3459 0.02255 0.01344 -0.2021 0.5875 0.4172
4.500 1.3695 0.02278 0.01376 -0.2013 0.5774 0.4195
4.750 1.3962 0.02287 0.01384 -0.2009 0.5695 0.4223
5.000 1.4187 0.02317 0.01429 -0.2000 0.5596 0.4255
5.250 1.4444 0.02333 0.01444 -0.1995 0.5516 0.4292
5.500 1.4669 0.02365 0.01486 -0.1986 0.5413 0.4327
5.750 1.4907 0.02387 0.01515 -0.1978 0.5324 0.4353
6.000 1.5132 0.02414 0.01552 -0.1968 0.5226 0.4379
6.250 1.5351 0.02445 0.01592 -0.1957 0.5127 0.4410
6.500 1.5579 0.02470 0.01619 -0.1947 0.5030 0.4448
6.750 1.5777 0.02511 0.01670 -0.1933 0.4913 0.4487
7.000 1.5975 0.02545 0.01714 -0.1918 0.4796 0.4518
7.250 1.6171 0.02581 0.01754 -0.1903 0.4675 0.4553
7.500 1.6353 0.02624 0.01803 -0.1886 0.4547 0.4589
7.750 1.6520 0.02677 0.01865 -0.1867 0.4415 0.4623
8.000 1.6675 0.02734 0.01927 -0.1846 0.4273 0.4656
8.250 1.6798 0.02799 0.01995 -0.1820 0.4104 0.4691
8.500 1.6879 0.02878 0.02074 -0.1789 0.3906 0.4729
8.750 1.6903 0.02973 0.02165 -0.1748 0.3698 0.4765
9.000 1.6927 0.03090 0.02281 -0.1712 0.3468 0.4801
9.250 1.6943 0.03223 0.02410 -0.1677 0.3248 0.4832
9.500 1.6958 0.03371 0.02553 -0.1645 0.3057 0.4866
9.750 1.6978 0.03530 0.02709 -0.1615 0.2893 0.4901
10.000 1.6991 0.03705 0.02881 -0.1587 0.2746 0.4938
10.250 1.7010 0.03886 0.03065 -0.1561 0.2613 0.4976
10.500 1.7030 0.04074 0.03257 -0.1536 0.2495 0.5020
10.750 1.7045 0.04273 0.03460 -0.1513 0.2393 0.5070
11.000 1.7070 0.04474 0.03670 -0.1492 0.2289 0.5126
11.250 1.7085 0.04688 0.03895 -0.1472 0.2187 0.5181
11.500 1.7070 0.04934 0.04147 -0.1452 0.2080 0.5241
11.750 1.7075 0.05177 0.04407 -0.1435 0.1955 0.5309
12.000 1.7060 0.05448 0.04692 -0.1419 0.1815 0.5383
12.250 1.7019 0.05754 0.05009 -0.1404 0.1638 0.5466
12.500 1.6944 0.06112 0.05370 -0.1391 0.1404 0.5562
12.750 1.6814 0.06549 0.05799 -0.1379 0.1178 0.5675
13.000 1.6681 0.07007 0.06251 -0.1369 0.1013 0.5859
13.250 1.6541 0.07430 0.06688 -0.1357 0.0912 0.8640
13.500 1.6413 0.07880 0.07139 -0.1349 0.0838 1.0000
13.750 1.6324 0.08321 0.07586 -0.1344 0.0778 1.0000
14.000 1.6227 0.08782 0.08052 -0.1342 0.0729 1.0000
14.250 1.6131 0.09255 0.08530 -0.1341 0.0692 1.0000
14.500 1.6070 0.09682 0.08971 -0.1342 0.0655 1.0000
14.750 1.5989 0.10146 0.09444 -0.1345 0.0624 1.0000
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Polar data table (+)
Polar graphs
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