GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Reynolds number: 100,000 Max Cl/Cd: 42.35 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe241-il-100000.txt Download as CSV file: xf-goe241-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 241 (MVA PR.1) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 0.1183 0.10932 0.10453 -0.1105 0.9047 0.1288
-9.000 0.1495 0.10555 0.10072 -0.1144 0.9019 0.1357
-8.750 0.1014 0.10764 0.10290 -0.1175 0.8861 0.1408
-8.500 0.1645 0.10028 0.09548 -0.1176 0.8861 0.1446
-8.250 0.1923 0.09685 0.09200 -0.1210 0.8831 0.1524
-8.000 0.1509 0.09751 0.09276 -0.1218 0.8671 0.1575
-7.750 0.2096 0.09196 0.08714 -0.1221 0.8663 0.1626
-7.500 0.2087 0.09097 0.08618 -0.1206 0.8542 0.1692
-7.250 0.2167 0.08790 0.08309 -0.1230 0.8485 0.1765
-7.000 0.2318 0.08628 0.08148 -0.1211 0.8383 0.1836
-6.750 0.2280 0.08419 0.07940 -0.1224 0.8303 0.1928
-6.500 0.2502 0.08219 0.07739 -0.1209 0.8218 0.2008
-6.250 0.2367 0.08096 0.07619 -0.1207 0.8120 0.2096
-6.000 0.2681 0.07821 0.07339 -0.1203 0.8060 0.2178
-5.750 0.2537 0.07741 0.07264 -0.1199 0.7939 0.2270
-5.500 0.2385 0.07829 0.07356 -0.1237 0.7796 0.2421
-5.250 0.2656 0.05137 0.04607 -0.1689 0.7730 0.1559
-5.000 0.3600 0.03846 0.03109 -0.1975 0.7663 0.1114
-4.750 0.3957 0.03609 0.02851 -0.1997 0.7581 0.1105
-4.500 0.4442 0.03348 0.02559 -0.2034 0.7542 0.1091
-4.250 0.4708 0.03256 0.02448 -0.2036 0.7438 0.1085
-4.000 0.5103 0.03110 0.02278 -0.2053 0.7376 0.1086
-3.750 0.5553 0.02972 0.02110 -0.2076 0.7336 0.1108
-3.500 0.5733 0.02944 0.02086 -0.2062 0.7216 0.1126
-3.250 0.6111 0.02816 0.01960 -0.2071 0.7166 0.1154
-3.000 0.6333 0.02800 0.01951 -0.2060 0.7067 0.1177
-2.750 0.6668 0.02735 0.01884 -0.2063 0.7000 0.1217
-2.500 0.7076 0.02644 0.01788 -0.2078 0.6957 0.1293
-2.250 0.7271 0.02676 0.01828 -0.2070 0.6844 0.1365
-2.000 0.7705 0.02591 0.01736 -0.2098 0.6794 0.1530
-1.750 0.8048 0.02549 0.01781 -0.2123 0.6712 0.3375
-1.500 0.8273 0.02665 0.01903 -0.2098 0.6643 0.4178
-1.250 0.8526 0.02770 0.01999 -0.2071 0.6599 0.4538
-1.000 0.8636 0.02908 0.02143 -0.2037 0.6510 0.4719
-0.750 0.8810 0.02992 0.02231 -0.2000 0.6452 0.4868
-0.500 0.9083 0.03025 0.02254 -0.1982 0.6413 0.5036
-0.250 0.9189 0.03136 0.02372 -0.1956 0.6334 0.5161
0.000 0.9430 0.03178 0.02408 -0.1946 0.6278 0.5328
0.250 0.9725 0.03178 0.02396 -0.1937 0.6237 0.5514
0.500 0.9843 0.03253 0.02479 -0.1909 0.6170 0.5619
0.750 1.0123 0.03263 0.02480 -0.1916 0.6103 0.5706
1.000 1.0515 0.03202 0.02399 -0.1934 0.6057 0.5762
1.250 1.0768 0.03243 0.02433 -0.1940 0.5992 0.5825
1.500 1.1000 0.03276 0.02464 -0.1939 0.5927 0.5887
1.750 1.1356 0.03243 0.02417 -0.1951 0.5883 0.5960
2.000 1.1723 0.03242 0.02398 -0.1973 0.5834 0.6039
2.250 1.1818 0.03325 0.02494 -0.1949 0.5760 0.6084
2.500 1.2181 0.03293 0.02447 -0.1964 0.5707 0.6170
2.750 1.2593 0.03242 0.02376 -0.1985 0.5662 0.6256
3.000 1.2629 0.03363 0.02514 -0.1955 0.5585 0.6316
3.250 1.2955 0.03362 0.02503 -0.1967 0.5533 0.6397
3.500 1.3339 0.03330 0.02458 -0.1983 0.5496 0.6481
3.750 1.3466 0.03444 0.02579 -0.1968 0.5439 0.6559
4.000 1.3588 0.03524 0.02670 -0.1949 0.5381 0.6623
4.250 1.3942 0.03515 0.02650 -0.1963 0.5336 0.6719
4.500 1.4388 0.03465 0.02583 -0.1988 0.5300 0.6813
4.750 1.4280 0.03666 0.02811 -0.1939 0.5229 0.6870
5.000 1.4511 0.03702 0.02848 -0.1935 0.5174 0.6955
5.250 1.4964 0.03640 0.02769 -0.1961 0.5131 0.7066
5.500 1.5029 0.03761 0.02901 -0.1934 0.5069 0.7135
5.750 1.5101 0.03859 0.03010 -0.1908 0.5001 0.7214
6.000 1.5559 0.03781 0.02915 -0.1933 0.4952 0.7332
6.250 1.5693 0.03865 0.03003 -0.1916 0.4890 0.7423
6.500 1.5675 0.03993 0.03144 -0.1877 0.4817 0.7496
6.750 1.6178 0.03896 0.03031 -0.1908 0.4765 0.7640
7.000 1.6169 0.04026 0.03175 -0.1870 0.4696 0.7728
7.250 1.6155 0.04134 0.03292 -0.1832 0.4623 0.7824
7.500 1.6830 0.03974 0.03112 -0.1885 0.4570 0.8027
7.750 1.6393 0.04266 0.03436 -0.1792 0.4485 0.8098
8.000 1.6682 0.04232 0.03403 -0.1792 0.4418 0.8331
8.250 1.7049 0.04161 0.03331 -0.1802 0.4356 1.0000
8.500 1.6643 0.04490 0.03683 -0.1724 0.4263 1.0000
8.750 1.7408 0.04281 0.03441 -0.1783 0.4207 1.0000
9.000 1.6774 0.04767 0.03961 -0.1685 0.4111 1.0000
9.250 1.7179 0.04703 0.03882 -0.1700 0.4051 1.0000
9.500 1.7330 0.04810 0.03984 -0.1690 0.3986 1.0000
9.750 1.6872 0.05292 0.04490 -0.1626 0.3901 1.0000
10.000 1.7530 0.05049 0.04222 -0.1659 0.3860 1.0000
10.250 1.6147 0.06377 0.05605 -0.1546 0.3746 1.0000
10.500 1.6566 0.06237 0.05455 -0.1552 0.3712 1.0000
10.750 1.7236 0.05908 0.05104 -0.1575 0.3689 1.0000
11.500 0.9951 0.18607 0.17996 -0.1780 0.3810 1.0000
11.750 0.9981 0.18840 0.18227 -0.1797 0.3754 1.0000
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Polar data table (+)
Polar graphs
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