GOE 225 (MVA H.35) AIRFOIL (goe225-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 225 (MVA H.35) AIRFOIL (goe225-il) Reynolds number: 1,000,000 Max Cl/Cd: 128.99 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe225-il-1000000-n5.txt Download as CSV file: xf-goe225-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4472 0.05510 0.05203 -0.1160 0.8243 0.0217
-11.750 -0.4638 0.04501 0.04175 -0.1301 0.8208 0.0218
-11.500 -0.4504 0.03695 0.03350 -0.1454 0.8179 0.0218
-11.250 -0.4193 0.02923 0.02553 -0.1628 0.8148 0.0220
-11.000 -0.3803 0.02428 0.02036 -0.1749 0.8120 0.0223
-10.750 -0.3412 0.02117 0.01708 -0.1830 0.8097 0.0225
-10.500 -0.3053 0.01932 0.01507 -0.1879 0.8076 0.0227
-10.250 -0.2725 0.01821 0.01384 -0.1908 0.8054 0.0228
-10.000 -0.2403 0.01729 0.01283 -0.1930 0.8036 0.0230
-9.750 -0.2084 0.01650 0.01196 -0.1949 0.8020 0.0232
-9.500 -0.1767 0.01579 0.01118 -0.1965 0.8003 0.0234
-9.250 -0.1454 0.01519 0.01051 -0.1979 0.7983 0.0237
-9.000 -0.1141 0.01465 0.00989 -0.1992 0.7962 0.0240
-8.750 -0.0829 0.01412 0.00928 -0.2003 0.7941 0.0242
-8.500 -0.0518 0.01361 0.00869 -0.2014 0.7918 0.0244
-8.250 -0.0208 0.01316 0.00815 -0.2024 0.7892 0.0246
-8.000 0.0102 0.01275 0.00765 -0.2033 0.7869 0.0248
-7.750 0.0414 0.01234 0.00720 -0.2043 0.7853 0.0250
-7.500 0.0724 0.01197 0.00677 -0.2051 0.7832 0.0252
-7.250 0.1034 0.01163 0.00639 -0.2059 0.7804 0.0254
-7.000 0.1342 0.01133 0.00603 -0.2066 0.7772 0.0255
-6.750 0.1649 0.01106 0.00569 -0.2072 0.7739 0.0257
-6.500 0.1961 0.01067 0.00523 -0.2081 0.7707 0.0260
-6.250 0.2274 0.01032 0.00484 -0.2089 0.7679 0.0264
-6.000 0.2584 0.01004 0.00454 -0.2096 0.7649 0.0268
-5.750 0.2892 0.00981 0.00427 -0.2103 0.7614 0.0272
-5.500 0.3198 0.00960 0.00403 -0.2108 0.7577 0.0276
-5.250 0.3503 0.00943 0.00381 -0.2113 0.7542 0.0280
-5.000 0.3808 0.00926 0.00361 -0.2118 0.7506 0.0285
-4.750 0.4114 0.00909 0.00342 -0.2123 0.7456 0.0290
-4.500 0.4417 0.00895 0.00324 -0.2127 0.7396 0.0294
-4.250 0.4719 0.00883 0.00307 -0.2131 0.7338 0.0298
-4.000 0.5021 0.00871 0.00291 -0.2136 0.7259 0.0302
-3.750 0.5322 0.00858 0.00273 -0.2139 0.7154 0.0310
-3.500 0.5617 0.00851 0.00259 -0.2142 0.6980 0.0320
-3.250 0.5901 0.00855 0.00249 -0.2142 0.6685 0.0330
-3.000 0.6176 0.00871 0.00246 -0.2141 0.6329 0.0342
-2.750 0.6451 0.00887 0.00246 -0.2140 0.6025 0.0364
-2.500 0.6733 0.00896 0.00245 -0.2141 0.5795 0.0417
-2.250 0.7021 0.00894 0.00246 -0.2144 0.5625 0.0704
-2.000 0.7306 0.00902 0.00249 -0.2145 0.5502 0.0787
-1.750 0.7592 0.00908 0.00253 -0.2146 0.5401 0.0851
-1.500 0.7878 0.00915 0.00256 -0.2147 0.5318 0.0880
-1.250 0.8164 0.00921 0.00258 -0.2148 0.5237 0.0918
-1.000 0.8449 0.00927 0.00262 -0.2149 0.5170 0.0960
-0.750 0.8737 0.00931 0.00264 -0.2150 0.5117 0.0993
-0.500 0.9022 0.00937 0.00268 -0.2151 0.5059 0.1024
-0.250 0.9305 0.00943 0.00272 -0.2151 0.5003 0.1082
0.000 0.9593 0.00946 0.00276 -0.2153 0.4958 0.1137
0.250 0.9878 0.00950 0.00280 -0.2154 0.4910 0.1213
0.500 1.0161 0.00953 0.00286 -0.2155 0.4859 0.1402
0.750 1.0452 0.00945 0.00295 -0.2159 0.4814 0.2209
1.000 1.0736 0.00949 0.00303 -0.2160 0.4770 0.2434
1.250 1.1013 0.00958 0.00313 -0.2159 0.4704 0.2585
1.500 1.1286 0.00970 0.00324 -0.2158 0.4626 0.2710
1.750 1.1560 0.00982 0.00334 -0.2157 0.4537 0.2812
2.000 1.1830 0.00995 0.00346 -0.2155 0.4464 0.2895
2.250 1.2105 0.01005 0.00355 -0.2155 0.4405 0.2966
2.500 1.2375 0.01018 0.00368 -0.2153 0.4343 0.3043
2.750 1.2644 0.01030 0.00380 -0.2151 0.4293 0.3142
3.000 1.2917 0.01038 0.00392 -0.2150 0.4246 0.3274
3.250 1.3183 0.01051 0.00406 -0.2148 0.4183 0.3388
3.500 1.3445 0.01066 0.00421 -0.2145 0.4121 0.3507
3.750 1.3712 0.01078 0.00436 -0.2143 0.4063 0.3666
4.000 1.3971 0.01093 0.00454 -0.2140 0.4001 0.3895
4.250 1.4229 0.01107 0.00472 -0.2137 0.3944 0.4137
4.500 1.4485 0.01123 0.00492 -0.2133 0.3870 0.4408
4.750 1.4730 0.01144 0.00514 -0.2127 0.3788 0.4602
5.000 1.4970 0.01168 0.00536 -0.2120 0.3679 0.4734
5.250 1.5201 0.01196 0.00561 -0.2112 0.3553 0.4841
5.500 1.5424 0.01228 0.00589 -0.2102 0.3428 0.4949
5.750 1.5638 0.01261 0.00619 -0.2091 0.3301 0.5044
6.000 1.5835 0.01303 0.00653 -0.2077 0.3134 0.5141
6.250 1.6012 0.01351 0.00694 -0.2059 0.2935 0.5245
6.500 1.6176 0.01402 0.00737 -0.2038 0.2754 0.5344
6.750 1.6309 0.01451 0.00781 -0.2012 0.2610 0.5444
7.000 1.6462 0.01503 0.00829 -0.1990 0.2481 0.5536
7.250 1.6616 0.01560 0.00882 -0.1969 0.2351 0.5641
7.500 1.6772 0.01618 0.00938 -0.1949 0.2228 0.5760
7.750 1.6942 0.01670 0.00990 -0.1932 0.2136 0.5915
8.000 1.7102 0.01729 0.01049 -0.1914 0.2050 0.6122
8.250 1.7282 0.01777 0.01104 -0.1899 0.1981 0.6486
8.500 1.7409 0.01804 0.01173 -0.1876 0.1891 1.0000
8.750 1.7548 0.01881 0.01245 -0.1856 0.1781 1.0000
9.000 1.7687 0.01959 0.01319 -0.1837 0.1681 1.0000
9.250 1.7817 0.02043 0.01399 -0.1816 0.1591 1.0000
9.500 1.7932 0.02140 0.01491 -0.1795 0.1479 1.0000
9.750 1.8039 0.02245 0.01590 -0.1773 0.1358 1.0000
10.000 1.8130 0.02362 0.01701 -0.1749 0.1231 1.0000
10.250 1.8186 0.02507 0.01836 -0.1722 0.1073 1.0000
10.500 1.8036 0.02808 0.02111 -0.1672 0.0655 1.0000
10.750 1.8068 0.02982 0.02282 -0.1645 0.0551 1.0000
11.000 1.8139 0.03129 0.02431 -0.1624 0.0504 1.0000
11.250 1.8235 0.03259 0.02564 -0.1605 0.0474 1.0000
11.500 1.8323 0.03396 0.02704 -0.1587 0.0450 1.0000
11.750 1.8395 0.03549 0.02860 -0.1567 0.0426 1.0000
12.000 1.8486 0.03690 0.03004 -0.1550 0.0408 1.0000
12.250 1.8567 0.03841 0.03160 -0.1534 0.0389 1.0000
12.500 1.8631 0.04012 0.03333 -0.1516 0.0366 1.0000
12.750 1.8694 0.04186 0.03511 -0.1499 0.0348 1.0000
13.000 1.8767 0.04355 0.03685 -0.1483 0.0331 1.0000
13.250 1.8814 0.04554 0.03887 -0.1467 0.0311 1.0000
13.500 1.8866 0.04752 0.04089 -0.1451 0.0295 1.0000
13.750 1.8912 0.04961 0.04303 -0.1437 0.0276 1.0000
14.000 1.8932 0.05200 0.04545 -0.1422 0.0255 1.0000
14.250 1.8965 0.05432 0.04783 -0.1408 0.0236 1.0000
14.500 1.8975 0.05697 0.05051 -0.1395 0.0217 1.0000
14.750 1.8987 0.05965 0.05325 -0.1384 0.0202 1.0000
15.000 1.8984 0.06258 0.05623 -0.1373 0.0187 1.0000
15.250 1.8976 0.06561 0.05932 -0.1363 0.0176 1.0000
15.500 1.8966 0.06872 0.06250 -0.1354 0.0166 1.0000
15.750 1.8945 0.07204 0.06589 -0.1347 0.0158 1.0000
16.000 1.8911 0.07560 0.06952 -0.1340 0.0150 1.0000
16.250 1.8889 0.07903 0.07303 -0.1335 0.0145 1.0000
16.500 1.8854 0.08264 0.07672 -0.1331 0.0140 1.0000
16.750 1.8809 0.08642 0.08058 -0.1327 0.0134 1.0000
17.000 1.8754 0.09038 0.08462 -0.1325 0.0130 1.0000
17.250 1.8688 0.09453 0.08885 -0.1324 0.0125 1.0000
17.500 1.8631 0.09859 0.09299 -0.1325 0.0121 1.0000
17.750 1.8577 0.10260 0.09709 -0.1326 0.0118 1.0000
18.000 1.8522 0.10661 0.10119 -0.1328 0.0115 1.0000
18.250 1.8464 0.11071 0.10538 -0.1331 0.0112 1.0000
18.500 1.8395 0.11503 0.10978 -0.1336 0.0109 1.0000
18.750 1.8330 0.11932 0.11415 -0.1343 0.0106 1.0000
19.000 1.8270 0.12354 0.11845 -0.1350 0.0104 1.0000
19.250 1.8194 0.12806 0.12305 -0.1359 0.0101 1.0000
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