GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Reynolds number: 500,000 Max Cl/Cd: 94.51 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe241-il-500000.txt Download as CSV file: xf-goe241-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 0.0981 0.10017 0.09706 -0.1048 0.8256 0.0380
-10.500 0.1074 0.09759 0.09448 -0.1061 0.8193 0.0387
-10.250 0.0837 0.08843 0.08528 -0.1156 0.8136 0.0414
-10.000 0.0975 0.08652 0.08333 -0.1148 0.8080 0.0417
-9.750 0.1118 0.08487 0.08169 -0.1148 0.8020 0.0419
-9.500 0.1252 0.08319 0.07997 -0.1150 0.7957 0.0422
-9.250 0.1378 0.08140 0.07813 -0.1155 0.7897 0.0427
-9.000 0.1490 0.07919 0.07594 -0.1167 0.7835 0.0433
-8.750 0.1116 0.06476 0.06151 -0.1309 0.7782 0.0472
-8.500 0.1282 0.06424 0.06093 -0.1299 0.7720 0.0474
-8.250 0.1433 0.06309 0.05980 -0.1299 0.7656 0.0476
-8.000 0.1562 0.06140 0.05810 -0.1306 0.7589 0.0480
-7.750 0.1671 0.05927 0.05592 -0.1318 0.7527 0.0485
-7.500 0.1702 0.03333 0.02898 -0.1897 0.7455 0.0536
-7.250 0.1938 0.03153 0.02723 -0.1901 0.7390 0.0542
-7.000 0.2203 0.03013 0.02577 -0.1914 0.7327 0.0550
-6.750 0.2648 0.02333 0.01808 -0.2013 0.7261 0.0458
-6.500 0.2969 0.02120 0.01572 -0.2036 0.7188 0.0446
-6.250 0.3294 0.01950 0.01376 -0.2055 0.7118 0.0441
-6.000 0.3609 0.01841 0.01250 -0.2068 0.7033 0.0444
-5.750 0.3919 0.01761 0.01151 -0.2077 0.6951 0.0450
-5.500 0.4227 0.01678 0.01055 -0.2086 0.6856 0.0453
-5.250 0.4529 0.01612 0.00974 -0.2091 0.6764 0.0456
-5.000 0.4831 0.01556 0.00908 -0.2097 0.6662 0.0461
-4.750 0.5129 0.01517 0.00855 -0.2101 0.6563 0.0465
-4.500 0.5427 0.01474 0.00802 -0.2105 0.6452 0.0470
-4.250 0.5717 0.01412 0.00739 -0.2109 0.6342 0.0479
-3.750 0.6299 0.01368 0.00685 -0.2115 0.6093 0.0501
-3.500 0.6591 0.01351 0.00660 -0.2118 0.5971 0.0513
-3.250 0.6878 0.01340 0.00638 -0.2120 0.5851 0.0523
-3.000 0.7173 0.01326 0.00617 -0.2124 0.5736 0.0532
-2.750 0.7476 0.01298 0.00585 -0.2132 0.5628 0.0549
-2.500 0.7768 0.01291 0.00570 -0.2136 0.5517 0.0566
-2.250 0.8061 0.01286 0.00559 -0.2140 0.5421 0.0588
-2.000 0.8357 0.01277 0.00542 -0.2145 0.5334 0.0613
-1.750 0.8654 0.01270 0.00530 -0.2150 0.5262 0.0645
-1.500 0.8946 0.01269 0.00523 -0.2153 0.5192 0.0677
-1.250 0.9237 0.01266 0.00511 -0.2157 0.5126 0.0734
-1.000 0.9534 0.01260 0.00505 -0.2162 0.5070 0.0836
-0.750 0.9880 0.01192 0.00497 -0.2185 0.5011 0.3324
-0.500 1.0152 0.01208 0.00513 -0.2183 0.4955 0.3721
-0.250 1.0424 0.01225 0.00529 -0.2182 0.4904 0.3929
0.000 1.0699 0.01239 0.00545 -0.2181 0.4854 0.4073
0.250 1.0967 0.01257 0.00560 -0.2179 0.4805 0.4186
0.500 1.1226 0.01282 0.00577 -0.2175 0.4755 0.4285
0.750 1.1496 0.01297 0.00594 -0.2173 0.4715 0.4376
1.000 1.1765 0.01313 0.00610 -0.2171 0.4673 0.4460
1.250 1.2027 0.01331 0.00624 -0.2168 0.4629 0.4535
1.500 1.2278 0.01355 0.00646 -0.2163 0.4586 0.4612
1.750 1.2534 0.01381 0.00667 -0.2159 0.4550 0.4694
2.000 1.2798 0.01393 0.00684 -0.2157 0.4517 0.4761
2.250 1.3054 0.01409 0.00701 -0.2153 0.4476 0.4812
2.500 1.3301 0.01430 0.00719 -0.2148 0.4435 0.4867
2.750 1.3542 0.01457 0.00738 -0.2142 0.4396 0.4917
3.000 1.3788 0.01476 0.00760 -0.2137 0.4362 0.4965
3.250 1.4036 0.01492 0.00781 -0.2132 0.4331 0.5014
3.500 1.4277 0.01512 0.00801 -0.2126 0.4298 0.5070
3.750 1.4508 0.01535 0.00821 -0.2118 0.4263 0.5121
4.000 1.4713 0.01559 0.00846 -0.2106 0.4228 0.5163
4.250 1.4910 0.01590 0.00875 -0.2092 0.4192 0.5206
4.500 1.5125 0.01609 0.00899 -0.2081 0.4164 0.5255
4.750 1.5346 0.01632 0.00924 -0.2073 0.4129 0.5304
5.000 1.5561 0.01658 0.00953 -0.2063 0.4092 0.5347
5.250 1.5762 0.01692 0.00987 -0.2052 0.4054 0.5390
5.500 1.5959 0.01733 0.01026 -0.2040 0.4014 0.5436
5.750 1.6177 0.01759 0.01056 -0.2032 0.3979 0.5483
6.000 1.6385 0.01788 0.01091 -0.2023 0.3937 0.5524
6.250 1.6574 0.01828 0.01132 -0.2010 0.3892 0.5566
6.500 1.6740 0.01880 0.01182 -0.1995 0.3844 0.5610
6.750 1.6946 0.01914 0.01221 -0.1986 0.3797 0.5656
7.000 1.7131 0.01957 0.01268 -0.1974 0.3738 0.5697
7.250 1.7273 0.02022 0.01331 -0.1957 0.3675 0.5736
7.500 1.7461 0.02067 0.01382 -0.1947 0.3608 0.5781
7.750 1.7602 0.02139 0.01452 -0.1930 0.3526 0.5825
8.000 1.7754 0.02208 0.01523 -0.1916 0.3436 0.5864
8.250 1.7855 0.02307 0.01620 -0.1896 0.3324 0.5903
8.500 1.7953 0.02416 0.01726 -0.1876 0.3184 0.5943
8.750 1.8020 0.02549 0.01855 -0.1854 0.3033 0.5984
9.000 1.8067 0.02702 0.02002 -0.1831 0.2895 0.6020
9.250 1.8113 0.02863 0.02158 -0.1809 0.2790 0.6056
9.500 1.8138 0.03043 0.02336 -0.1786 0.2704 0.6093
9.750 1.8216 0.03187 0.02482 -0.1769 0.2647 0.6136
10.000 1.8276 0.03350 0.02646 -0.1751 0.2598 0.6177
10.250 1.8311 0.03538 0.02833 -0.1732 0.2554 0.6212
10.500 1.8395 0.03688 0.02990 -0.1718 0.2524 0.6253
10.750 1.8491 0.03832 0.03141 -0.1706 0.2499 0.6300
11.000 1.8575 0.03989 0.03303 -0.1693 0.2474 0.6349
11.250 1.8635 0.04170 0.03488 -0.1679 0.2445 0.6394
11.500 1.8674 0.04374 0.03695 -0.1664 0.2415 0.6439
11.750 1.8695 0.04592 0.03914 -0.1648 0.2382 0.6486
12.000 1.8795 0.04747 0.04079 -0.1639 0.2364 0.6545
12.250 1.8888 0.04910 0.04253 -0.1630 0.2345 0.6610
12.500 1.8970 0.05086 0.04438 -0.1621 0.2327 0.6687
12.750 1.9035 0.05280 0.04640 -0.1611 0.2307 0.6772
13.000 1.9089 0.05486 0.04854 -0.1602 0.2287 0.6885
13.250 1.9127 0.05711 0.05087 -0.1592 0.2265 0.7074
13.500 1.9145 0.05892 0.05296 -0.1576 0.2243 1.0000
13.750 1.9206 0.06086 0.05492 -0.1566 0.2223 1.0000
14.000 1.9284 0.06278 0.05692 -0.1560 0.2213 1.0000
14.250 1.9348 0.06487 0.05910 -0.1553 0.2200 1.0000
14.500 1.9411 0.06696 0.06127 -0.1547 0.2185 1.0000
14.750 1.9458 0.06923 0.06361 -0.1541 0.2168 1.0000
15.000 1.9495 0.07162 0.06605 -0.1534 0.2147 1.0000
15.250 1.9513 0.07423 0.06870 -0.1528 0.2126 1.0000
15.500 1.9536 0.07673 0.07122 -0.1521 0.2104 1.0000
15.750 1.9585 0.07878 0.07327 -0.1513 0.2081 1.0000
16.000 1.9622 0.08121 0.07578 -0.1509 0.2064 1.0000
16.250 1.9646 0.08390 0.07859 -0.1506 0.2049 1.0000
16.500 1.9655 0.08678 0.08157 -0.1503 0.2029 1.0000
16.750 1.9670 0.08954 0.08442 -0.1501 0.2008 1.0000
17.000 1.9673 0.09246 0.08740 -0.1499 0.1987 1.0000
17.250 1.9671 0.09540 0.09038 -0.1497 0.1963 1.0000
17.500 1.9662 0.09834 0.09332 -0.1494 0.1933 1.0000
17.750 1.9666 0.10130 0.09639 -0.1494 0.1910 1.0000
18.000 1.9644 0.10471 0.09992 -0.1496 0.1885 1.0000
18.250 1.9632 0.10791 0.10322 -0.1498 0.1855 1.0000
18.500 1.9597 0.11140 0.10676 -0.1500 0.1822 1.0000
18.750 1.9534 0.11526 0.11062 -0.1503 0.1785 1.0000
19.000 1.9526 0.11847 0.11396 -0.1508 0.1748 1.0000
19.250 1.9477 0.12226 0.11784 -0.1514 0.1697 1.0000
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