GOE 227 (MVA H.37) AIRFOIL (goe227-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 227 (MVA H.37) AIRFOIL (goe227-il) Reynolds number: 500,000 Max Cl/Cd: 131.66 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe227-il-500000.txt Download as CSV file: xf-goe227-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 227 (MVA H.37) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.0159 0.09750 0.09446 -0.0979 0.8356 0.0441
-9.750 -0.0065 0.09510 0.09201 -0.0990 0.8276 0.0454
-9.500 -0.1831 0.02583 0.02170 -0.1860 0.8183 0.0416
-9.250 -0.1481 0.02212 0.01751 -0.1939 0.8103 0.0425
-9.000 -0.1183 0.02086 0.01613 -0.1961 0.8027 0.0433
-8.750 -0.0888 0.02031 0.01552 -0.1974 0.7937 0.0441
-8.500 -0.0585 0.01966 0.01473 -0.1988 0.7849 0.0451
-8.250 -0.0277 0.01873 0.01362 -0.2005 0.7750 0.0461
-8.000 0.0035 0.01778 0.01245 -0.2022 0.7648 0.0472
-7.750 0.0344 0.01704 0.01147 -0.2036 0.7548 0.0481
-7.500 0.0655 0.01586 0.01012 -0.2053 0.7439 0.0494
-7.250 0.0954 0.01546 0.00966 -0.2060 0.7343 0.0505
-7.000 0.1252 0.01522 0.00933 -0.2067 0.7250 0.0519
-6.750 0.1555 0.01489 0.00888 -0.2074 0.7170 0.0535
-6.500 0.1860 0.01454 0.00836 -0.2082 0.7096 0.0550
-6.250 0.2170 0.01388 0.00757 -0.2093 0.7038 0.0567
-6.000 0.2473 0.01360 0.00727 -0.2100 0.6985 0.0585
-5.750 0.2774 0.01343 0.00703 -0.2106 0.6939 0.0605
-5.500 0.3077 0.01330 0.00676 -0.2111 0.6901 0.0628
-5.250 0.3387 0.01290 0.00629 -0.2120 0.6867 0.0652
-5.000 0.3691 0.01265 0.00605 -0.2127 0.6828 0.0678
-4.750 0.3992 0.01253 0.00586 -0.2132 0.6788 0.0704
-4.500 0.4292 0.01246 0.00567 -0.2137 0.6747 0.0729
-4.250 0.4602 0.01208 0.00525 -0.2146 0.6713 0.0761
-4.000 0.4906 0.01192 0.00510 -0.2152 0.6681 0.0793
-3.750 0.5208 0.01181 0.00496 -0.2157 0.6653 0.0824
-3.500 0.5509 0.01177 0.00483 -0.2161 0.6626 0.0848
-3.250 0.5820 0.01148 0.00451 -0.2170 0.6596 0.0890
-3.000 0.6123 0.01144 0.00443 -0.2176 0.6564 0.0925
-2.750 0.6424 0.01135 0.00434 -0.2180 0.6540 0.0961
-2.500 0.6729 0.01122 0.00419 -0.2186 0.6518 0.0996
-2.250 0.7035 0.01110 0.00409 -0.2193 0.6494 0.1047
-2.000 0.7334 0.01107 0.00403 -0.2197 0.6468 0.1095
-1.750 0.7637 0.01101 0.00394 -0.2202 0.6441 0.1152
-1.500 0.7940 0.01101 0.00393 -0.2208 0.6417 0.1236
-1.250 0.8245 0.01097 0.00390 -0.2214 0.6392 0.1360
-1.000 0.8547 0.01084 0.00384 -0.2220 0.6366 0.1574
-0.750 0.8860 0.01055 0.00385 -0.2230 0.6336 0.2562
-0.500 0.9153 0.01058 0.00396 -0.2233 0.6308 0.3055
-0.250 0.9444 0.01066 0.00404 -0.2236 0.6284 0.3250
0.000 0.9735 0.01076 0.00413 -0.2238 0.6259 0.3396
0.250 1.0029 0.01094 0.00426 -0.2241 0.6229 0.3514
0.500 1.0314 0.01098 0.00433 -0.2242 0.6205 0.3622
0.750 1.0600 0.01101 0.00441 -0.2244 0.6176 0.3710
1.000 1.0885 0.01108 0.00449 -0.2245 0.6147 0.3803
1.250 1.1172 0.01113 0.00456 -0.2247 0.6118 0.3893
1.500 1.1458 0.01123 0.00464 -0.2248 0.6087 0.3983
1.750 1.1747 0.01138 0.00479 -0.2251 0.6051 0.4090
2.000 1.2024 0.01139 0.00486 -0.2251 0.6019 0.4189
2.250 1.2303 0.01140 0.00495 -0.2251 0.5981 0.4294
2.500 1.2583 0.01144 0.00503 -0.2252 0.5944 0.4411
2.750 1.2863 0.01152 0.00511 -0.2252 0.5905 0.4538
3.000 1.3141 0.01160 0.00524 -0.2253 0.5863 0.4690
3.250 1.3410 0.01159 0.00534 -0.2251 0.5814 0.4875
3.500 1.3680 0.01161 0.00543 -0.2250 0.5763 0.5094
3.750 1.3952 0.01170 0.00554 -0.2249 0.5713 0.5333
4.000 1.4215 0.01170 0.00566 -0.2246 0.5653 0.5567
4.250 1.4475 0.01171 0.00574 -0.2243 0.5581 0.5786
4.500 1.4733 0.01175 0.00584 -0.2240 0.5501 0.6006
4.750 1.4982 0.01178 0.00593 -0.2234 0.5394 0.6239
5.000 1.5228 0.01180 0.00605 -0.2229 0.5252 0.6527
5.250 1.5449 0.01188 0.00623 -0.2219 0.5051 0.7078
5.500 1.5589 0.01184 0.00641 -0.2191 0.4801 1.0000
5.750 1.5757 0.01239 0.00679 -0.2172 0.4585 1.0000
6.000 1.5930 0.01295 0.00723 -0.2154 0.4429 1.0000
6.250 1.6114 0.01345 0.00765 -0.2138 0.4312 1.0000
6.500 1.6296 0.01394 0.00810 -0.2122 0.4217 1.0000
6.750 1.6443 0.01450 0.00859 -0.2099 0.4122 1.0000
7.000 1.6609 0.01495 0.00903 -0.2080 0.4032 1.0000
7.500 1.6926 0.01599 0.01004 -0.2041 0.3873 1.0000
7.750 1.7074 0.01658 0.01060 -0.2021 0.3802 1.0000
8.000 1.7241 0.01710 0.01114 -0.2004 0.3734 1.0000
8.250 1.7399 0.01766 0.01171 -0.1986 0.3662 1.0000
8.500 1.7536 0.01836 0.01240 -0.1966 0.3595 1.0000
8.750 1.7700 0.01892 0.01300 -0.1951 0.3517 1.0000
9.000 1.7813 0.01979 0.01383 -0.1928 0.3439 1.0000
9.250 1.7979 0.02039 0.01449 -0.1914 0.3363 1.0000
9.750 1.8228 0.02214 0.01627 -0.1876 0.3191 1.0000
10.000 1.8322 0.02327 0.01738 -0.1854 0.3082 1.0000
10.250 1.8392 0.02460 0.01868 -0.1831 0.2957 1.0000
10.500 1.8450 0.02607 0.02011 -0.1808 0.2806 1.0000
10.750 1.8477 0.02785 0.02183 -0.1782 0.2600 1.0000
11.000 1.8407 0.03042 0.02427 -0.1748 0.2328 1.0000
11.250 1.8246 0.03385 0.02748 -0.1708 0.1968 1.0000
11.500 1.7999 0.03819 0.03156 -0.1665 0.1552 1.0000
11.750 1.7759 0.04277 0.03593 -0.1626 0.1221 1.0000
12.000 1.7563 0.04721 0.04021 -0.1595 0.0937 1.0000
12.250 1.7282 0.05280 0.04557 -0.1564 0.0520 1.0000
12.500 1.7121 0.05738 0.05011 -0.1542 0.0372 1.0000
12.750 1.7078 0.06075 0.05354 -0.1528 0.0327 1.0000
13.000 1.7041 0.06412 0.05697 -0.1515 0.0301 1.0000
13.250 1.7036 0.06715 0.06009 -0.1504 0.0285 1.0000
13.500 1.7005 0.07051 0.06352 -0.1494 0.0271 1.0000
13.750 1.6941 0.07432 0.06741 -0.1483 0.0259 1.0000
14.000 1.6917 0.07771 0.07089 -0.1474 0.0250 1.0000
14.250 1.6900 0.08103 0.07430 -0.1467 0.0242 1.0000
14.500 1.6868 0.08457 0.07793 -0.1460 0.0234 1.0000
14.750 1.6817 0.08841 0.08186 -0.1454 0.0228 1.0000
15.000 1.6747 0.09257 0.08611 -0.1449 0.0223 1.0000
15.250 1.6645 0.09727 0.09091 -0.1445 0.0217 1.0000
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Polar data table (+)
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