GOE 227 (MVA H.37) AIRFOIL (goe227-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 227 (MVA H.37) AIRFOIL (goe227-il) Reynolds number: 100,000 Max Cl/Cd: 58.64 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe227-il-100000-n5.txt Download as CSV file: xf-goe227-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0480 0.12041 0.11505 -0.0971 0.9258 0.0760
-10.750 -0.0429 0.11744 0.11205 -0.1006 0.9190 0.0763
-10.500 -0.0361 0.11421 0.10881 -0.1028 0.9102 0.0763
-10.000 -0.0195 0.10743 0.10196 -0.1070 0.8943 0.0764
-9.500 0.0048 0.09837 0.09280 -0.1084 0.8803 0.0651
-9.250 0.0188 0.09540 0.08978 -0.1091 0.8737 0.0641
-9.000 0.0271 0.09248 0.08682 -0.1102 0.8653 0.0632
-8.750 0.0343 0.08941 0.08371 -0.1117 0.8575 0.0626
-8.500 0.0398 0.08636 0.08064 -0.1134 0.8494 0.0632
-8.250 0.0441 0.08316 0.07742 -0.1154 0.8409 0.0639
-8.000 0.0494 0.07992 0.07414 -0.1173 0.8333 0.0640
-7.750 0.0542 0.07688 0.07108 -0.1187 0.8246 0.0638
-7.500 0.0590 0.07360 0.06775 -0.1206 0.8179 0.0637
-7.250 0.0605 0.07049 0.06464 -0.1224 0.8086 0.0637
-6.750 0.0612 0.04954 0.04348 -0.1520 0.7916 0.0660
-6.500 0.0994 0.03992 0.03340 -0.1724 0.7858 0.0675
-6.250 0.1351 0.03587 0.02897 -0.1812 0.7798 0.0693
-6.000 0.1731 0.03260 0.02525 -0.1886 0.7740 0.0724
-5.750 0.2188 0.02904 0.02081 -0.1968 0.7700 0.0764
-5.500 0.2516 0.02770 0.01934 -0.1990 0.7667 0.0784
-5.250 0.2798 0.02697 0.01852 -0.2002 0.7609 0.0808
-5.000 0.3117 0.02611 0.01743 -0.2020 0.7565 0.0846
-4.750 0.3468 0.02505 0.01593 -0.2042 0.7531 0.0886
-4.500 0.3785 0.02427 0.01513 -0.2055 0.7504 0.0917
-4.250 0.4060 0.02398 0.01479 -0.2060 0.7457 0.0956
-4.000 0.4363 0.02349 0.01412 -0.2070 0.7415 0.1000
-3.750 0.4673 0.02296 0.01346 -0.2079 0.7381 0.1039
-3.500 0.4983 0.02259 0.01307 -0.2088 0.7354 0.1086
-3.250 0.5281 0.02231 0.01268 -0.2094 0.7323 0.1134
-3.000 0.5560 0.02214 0.01246 -0.2098 0.7285 0.1180
-2.750 0.5848 0.02197 0.01232 -0.2104 0.7252 0.1236
-2.500 0.6151 0.02174 0.01199 -0.2109 0.7219 0.1297
-2.250 0.6473 0.02136 0.01157 -0.2118 0.7187 0.1363
-2.000 0.6743 0.02129 0.01149 -0.2120 0.7131 0.1450
-1.750 0.7035 0.02106 0.01127 -0.2124 0.7080 0.1546
-1.500 0.7356 0.02073 0.01092 -0.2133 0.7041 0.1686
-1.250 0.7673 0.02046 0.01076 -0.2144 0.7003 0.1948
-1.000 0.7945 0.02047 0.01107 -0.2147 0.6947 0.2538
-0.750 0.8238 0.02049 0.01107 -0.2149 0.6900 0.3084
-0.500 0.8551 0.02047 0.01097 -0.2153 0.6863 0.3425
-0.250 0.8804 0.02074 0.01124 -0.2149 0.6814 0.3664
0.000 0.9070 0.02095 0.01143 -0.2148 0.6769 0.3865
0.250 0.9355 0.02105 0.01155 -0.2148 0.6730 0.4089
0.500 0.9658 0.02110 0.01156 -0.2151 0.6698 0.4312
0.750 0.9899 0.02142 0.01195 -0.2145 0.6649 0.4485
1.000 1.0157 0.02163 0.01217 -0.2142 0.6601 0.4618
1.250 1.0448 0.02170 0.01219 -0.2143 0.6559 0.4750
1.500 1.0760 0.02169 0.01214 -0.2148 0.6525 0.4877
1.750 1.0977 0.02207 0.01260 -0.2139 0.6466 0.4990
2.000 1.1241 0.02225 0.01276 -0.2137 0.6414 0.5113
2.250 1.1539 0.02226 0.01274 -0.2139 0.6371 0.5223
2.500 1.1798 0.02247 0.01296 -0.2136 0.6320 0.5339
2.750 1.2026 0.02277 0.01332 -0.2128 0.6257 0.5470
3.000 1.2310 0.02282 0.01335 -0.2128 0.6205 0.5619
3.250 1.2581 0.02294 0.01348 -0.2126 0.6152 0.5794
3.500 1.2781 0.02330 0.01396 -0.2114 0.6080 0.5979
3.750 1.3055 0.02333 0.01404 -0.2112 0.6024 0.6197
4.000 1.3284 0.02352 0.01434 -0.2104 0.5959 0.6450
4.250 1.3478 0.02376 0.01476 -0.2089 0.5880 0.6766
4.750 1.3817 0.02385 0.01529 -0.2048 0.5731 1.0000
5.000 1.4080 0.02401 0.01539 -0.2045 0.5662 1.0000
5.250 1.4220 0.02461 0.01607 -0.2024 0.5563 1.0000
5.500 1.4462 0.02476 0.01618 -0.2017 0.5486 1.0000
5.750 1.4563 0.02547 0.01698 -0.1991 0.5372 1.0000
6.000 1.4723 0.02593 0.01747 -0.1972 0.5276 1.0000
6.250 1.4879 0.02635 0.01791 -0.1953 0.5180 1.0000
6.500 1.4968 0.02705 0.01866 -0.1924 0.5071 1.0000
6.750 1.5127 0.02751 0.01910 -0.1905 0.4978 1.0000
7.000 1.5282 0.02801 0.01960 -0.1887 0.4885 1.0000
7.250 1.5432 0.02861 0.02020 -0.1869 0.4796 1.0000
7.500 1.5622 0.02902 0.02056 -0.1855 0.4720 1.0000
7.750 1.5767 0.02975 0.02130 -0.1838 0.4639 1.0000
8.000 1.5955 0.03024 0.02176 -0.1825 0.4568 1.0000
8.250 1.6104 0.03103 0.02256 -0.1808 0.4495 1.0000
8.500 1.6275 0.03172 0.02325 -0.1794 0.4429 1.0000
8.750 1.6495 0.03218 0.02367 -0.1786 0.4375 1.0000
9.000 1.6608 0.03328 0.02488 -0.1767 0.4309 1.0000
9.250 1.6805 0.03389 0.02548 -0.1756 0.4250 1.0000
9.500 1.6987 0.03463 0.02624 -0.1745 0.4191 1.0000
9.750 1.7091 0.03581 0.02752 -0.1726 0.4125 1.0000
10.000 1.7311 0.03632 0.02801 -0.1718 0.4065 1.0000
10.250 1.7362 0.03777 0.02958 -0.1694 0.3988 1.0000
10.500 1.7472 0.03877 0.03056 -0.1674 0.3894 1.0000
10.750 1.7451 0.04067 0.03258 -0.1645 0.3801 1.0000
11.000 1.7522 0.04189 0.03375 -0.1623 0.3696 1.0000
11.250 1.7438 0.04440 0.03644 -0.1592 0.3599 1.0000
11.500 1.7452 0.04619 0.03826 -0.1569 0.3502 1.0000
11.750 1.7406 0.04863 0.04085 -0.1545 0.3410 1.0000
12.000 1.7396 0.05082 0.04312 -0.1524 0.3321 1.0000
12.250 1.7357 0.05338 0.04578 -0.1504 0.3228 1.0000
12.500 1.7312 0.05617 0.04870 -0.1485 0.3136 1.0000
12.750 1.7291 0.05874 0.05133 -0.1469 0.3043 1.0000
13.000 1.7223 0.06213 0.05490 -0.1454 0.2951 1.0000
13.250 1.7176 0.06526 0.05811 -0.1440 0.2851 1.0000
13.500 1.7093 0.06899 0.06196 -0.1429 0.2737 1.0000
13.750 1.6997 0.07305 0.06615 -0.1419 0.2615 1.0000
14.000 1.6902 0.07718 0.07037 -0.1410 0.2484 1.0000
14.250 1.6796 0.08151 0.07477 -0.1403 0.2340 1.0000
14.500 1.6665 0.08626 0.07954 -0.1397 0.2169 1.0000
14.750 1.6500 0.09156 0.08479 -0.1393 0.1970 1.0000
15.000 1.6309 0.09736 0.09054 -0.1391 0.1747 1.0000
15.250 1.6092 0.10371 0.09679 -0.1394 0.1543 1.0000
15.500 1.5876 0.11029 0.10330 -0.1400 0.1368 1.0000
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