GOE 225 (MVA H.35) AIRFOIL (goe225-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 225 (MVA H.35) AIRFOIL (goe225-il) Reynolds number: 500,000 Max Cl/Cd: 107.48 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe225-il-500000-n5.txt Download as CSV file: xf-goe225-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 225 (MVA H.35) 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.1254 0.10454 0.10135 -0.0860 0.8534 0.0220
-10.250 -0.3075 0.03786 0.03393 -0.1483 0.8374 0.0258
-10.000 -0.2703 0.02937 0.02508 -0.1683 0.8341 0.0261
-9.750 -0.2296 0.02528 0.02075 -0.1791 0.8315 0.0263
-9.500 -0.1929 0.02298 0.01825 -0.1853 0.8291 0.0266
-9.250 -0.1596 0.02151 0.01662 -0.1889 0.8266 0.0269
-9.000 -0.1271 0.02035 0.01531 -0.1916 0.8246 0.0272
-8.750 -0.0950 0.01936 0.01416 -0.1939 0.8225 0.0276
-8.500 -0.0630 0.01840 0.01308 -0.1960 0.8201 0.0280
-8.250 -0.0312 0.01754 0.01210 -0.1977 0.8174 0.0283
-8.000 0.0004 0.01678 0.01122 -0.1993 0.8151 0.0286
-7.750 0.0318 0.01611 0.01043 -0.2006 0.8128 0.0289
-7.500 0.0631 0.01551 0.00972 -0.2018 0.8103 0.0291
-7.250 0.0941 0.01498 0.00908 -0.2028 0.8076 0.0294
-7.000 0.1251 0.01452 0.00850 -0.2037 0.8048 0.0297
-6.750 0.1561 0.01408 0.00799 -0.2046 0.8022 0.0299
-6.500 0.1875 0.01353 0.00741 -0.2057 0.7992 0.0303
-6.250 0.2187 0.01304 0.00688 -0.2067 0.7956 0.0308
-6.000 0.2497 0.01266 0.00644 -0.2075 0.7921 0.0313
-5.750 0.2805 0.01234 0.00607 -0.2082 0.7891 0.0319
-5.500 0.3114 0.01206 0.00573 -0.2089 0.7865 0.0326
-5.250 0.3423 0.01177 0.00541 -0.2096 0.7836 0.0332
-5.000 0.3731 0.01151 0.00512 -0.2103 0.7801 0.0337
-4.750 0.4037 0.01128 0.00484 -0.2108 0.7763 0.0343
-4.500 0.4341 0.01107 0.00457 -0.2113 0.7725 0.0349
-4.250 0.4649 0.01084 0.00428 -0.2119 0.7690 0.0359
-4.000 0.4954 0.01063 0.00407 -0.2125 0.7646 0.0371
-3.750 0.5257 0.01045 0.00387 -0.2129 0.7594 0.0386
-3.500 0.5557 0.01031 0.00367 -0.2133 0.7541 0.0405
-3.250 0.5861 0.01011 0.00349 -0.2138 0.7483 0.0455
-3.000 0.6164 0.00990 0.00337 -0.2143 0.7413 0.0644
-2.750 0.6458 0.00983 0.00329 -0.2145 0.7336 0.0777
-2.500 0.6751 0.00977 0.00322 -0.2147 0.7226 0.0854
-2.250 0.7041 0.00973 0.00314 -0.2148 0.7087 0.0908
-2.000 0.7325 0.00971 0.00305 -0.2148 0.6894 0.0955
-1.750 0.7596 0.00980 0.00298 -0.2145 0.6616 0.0996
-1.500 0.7858 0.00998 0.00297 -0.2141 0.6304 0.1031
-1.250 0.8120 0.01017 0.00301 -0.2138 0.6048 0.1088
-1.000 0.8388 0.01035 0.00307 -0.2135 0.5861 0.1136
-0.750 0.8658 0.01049 0.00313 -0.2133 0.5718 0.1185
-0.500 0.8935 0.01058 0.00318 -0.2133 0.5597 0.1271
-0.250 0.9211 0.01066 0.00325 -0.2133 0.5496 0.1432
0.000 0.9491 0.01065 0.00336 -0.2135 0.5406 0.2049
0.250 0.9767 0.01074 0.00348 -0.2134 0.5336 0.2402
0.500 1.0042 0.01085 0.00359 -0.2133 0.5266 0.2604
0.750 1.0311 0.01100 0.00373 -0.2131 0.5199 0.2763
1.000 1.0586 0.01110 0.00384 -0.2130 0.5144 0.2876
1.250 1.0859 0.01123 0.00395 -0.2129 0.5087 0.2975
1.500 1.1126 0.01138 0.00409 -0.2127 0.5031 0.3075
1.750 1.1396 0.01151 0.00422 -0.2125 0.4981 0.3168
2.000 1.1667 0.01161 0.00436 -0.2123 0.4923 0.3274
2.250 1.1924 0.01180 0.00453 -0.2119 0.4846 0.3387
2.500 1.2188 0.01194 0.00467 -0.2116 0.4765 0.3512
2.750 1.2445 0.01211 0.00486 -0.2112 0.4684 0.3666
3.000 1.2705 0.01226 0.00503 -0.2109 0.4626 0.3836
3.250 1.2967 0.01239 0.00521 -0.2106 0.4566 0.4042
3.500 1.3220 0.01257 0.00542 -0.2101 0.4507 0.4255
3.750 1.3474 0.01273 0.00563 -0.2097 0.4455 0.4477
4.000 1.3731 0.01288 0.00583 -0.2093 0.4402 0.4689
4.250 1.3977 0.01308 0.00605 -0.2087 0.4342 0.4846
4.500 1.4220 0.01329 0.00627 -0.2081 0.4284 0.4979
4.750 1.4467 0.01346 0.00649 -0.2075 0.4221 0.5103
5.000 1.4700 0.01370 0.00674 -0.2067 0.4160 0.5218
5.250 1.4937 0.01391 0.00699 -0.2060 0.4103 0.5341
5.500 1.5167 0.01413 0.00724 -0.2051 0.4033 0.5474
5.750 1.5379 0.01442 0.00755 -0.2039 0.3954 0.5602
6.000 1.5586 0.01471 0.00785 -0.2027 0.3849 0.5729
6.250 1.5775 0.01505 0.00819 -0.2011 0.3738 0.5863
6.500 1.5925 0.01544 0.00859 -0.1987 0.3630 0.6019
6.750 1.6094 0.01585 0.00903 -0.1969 0.3504 0.6244
7.000 1.6269 0.01627 0.00953 -0.1952 0.3368 0.6743
7.250 1.6388 0.01645 0.00999 -0.1923 0.3238 1.0000
7.500 1.6533 0.01712 0.01060 -0.1902 0.3085 1.0000
7.750 1.6672 0.01784 0.01125 -0.1881 0.2931 1.0000
8.000 1.6807 0.01862 0.01196 -0.1859 0.2785 1.0000
8.250 1.6935 0.01946 0.01274 -0.1838 0.2638 1.0000
8.500 1.7059 0.02035 0.01358 -0.1816 0.2503 1.0000
8.750 1.7184 0.02126 0.01444 -0.1795 0.2380 1.0000
9.000 1.7322 0.02210 0.01527 -0.1777 0.2283 1.0000
9.250 1.7446 0.02305 0.01620 -0.1757 0.2196 1.0000
9.500 1.7573 0.02400 0.01713 -0.1738 0.2101 1.0000
9.750 1.7682 0.02508 0.01819 -0.1718 0.2002 1.0000
10.000 1.7773 0.02632 0.01939 -0.1696 0.1892 1.0000
10.250 1.7866 0.02757 0.02060 -0.1675 0.1775 1.0000
10.500 1.7964 0.02878 0.02181 -0.1655 0.1683 1.0000
10.750 1.8048 0.03013 0.02314 -0.1634 0.1594 1.0000
11.000 1.8134 0.03149 0.02449 -0.1614 0.1501 1.0000
11.250 1.8210 0.03295 0.02594 -0.1594 0.1408 1.0000
11.500 1.8257 0.03464 0.02760 -0.1571 0.1293 1.0000
11.750 1.8265 0.03671 0.02961 -0.1546 0.1135 1.0000
12.000 1.8099 0.04038 0.03305 -0.1508 0.0766 1.0000
12.250 1.7990 0.04371 0.03630 -0.1477 0.0598 1.0000
12.500 1.7993 0.04614 0.03876 -0.1457 0.0545 1.0000
12.750 1.8003 0.04856 0.04122 -0.1439 0.0508 1.0000
13.000 1.8030 0.05086 0.04360 -0.1423 0.0482 1.0000
13.250 1.8058 0.05323 0.04603 -0.1409 0.0458 1.0000
13.500 1.8066 0.05588 0.04875 -0.1395 0.0436 1.0000
13.750 1.8069 0.05867 0.05161 -0.1382 0.0417 1.0000
14.000 1.8097 0.06122 0.05425 -0.1371 0.0400 1.0000
14.250 1.8103 0.06410 0.05721 -0.1361 0.0381 1.0000
14.500 1.8086 0.06731 0.06048 -0.1352 0.0363 1.0000
14.750 1.8077 0.07050 0.06376 -0.1344 0.0347 1.0000
15.000 1.8072 0.07370 0.06704 -0.1337 0.0330 1.0000
15.250 1.8046 0.07721 0.07063 -0.1332 0.0313 1.0000
15.500 1.8010 0.08089 0.07439 -0.1327 0.0298 1.0000
15.750 1.7986 0.08444 0.07803 -0.1324 0.0284 1.0000
16.000 1.7947 0.08824 0.08191 -0.1322 0.0268 1.0000
16.250 1.7892 0.09229 0.08603 -0.1320 0.0255 1.0000
16.500 1.7855 0.09612 0.08995 -0.1320 0.0242 1.0000
16.750 1.7804 0.10016 0.09408 -0.1321 0.0229 1.0000
17.000 1.7737 0.10444 0.09844 -0.1323 0.0218 1.0000
17.250 1.7680 0.10861 0.10270 -0.1327 0.0209 1.0000
17.500 1.7626 0.11278 0.10696 -0.1331 0.0199 1.0000
17.750 1.7567 0.11705 0.11131 -0.1337 0.0189 1.0000
18.000 1.7496 0.12156 0.11589 -0.1345 0.0182 1.0000
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