GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 241 (MVA PR.1) AIRFOIL (goe241-il) Reynolds number: 500,000 Max Cl/Cd: 91.66 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe241-il-500000-n5.txt Download as CSV file: xf-goe241-il-500000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.1863 0.04118 0.03705 -0.1465 0.7642 0.0277
-10.500 -0.1841 0.03639 0.03206 -0.1546 0.7578 0.0278
-10.250 -0.1658 0.03296 0.02846 -0.1620 0.7524 0.0280
-10.000 -0.1395 0.03013 0.02548 -0.1691 0.7468 0.0282
-9.750 -0.1086 0.02774 0.02292 -0.1758 0.7405 0.0284
-9.500 -0.0750 0.02569 0.02066 -0.1818 0.7344 0.0286
-9.250 -0.0408 0.02393 0.01873 -0.1869 0.7281 0.0289
-9.000 -0.0087 0.02252 0.01715 -0.1903 0.7213 0.0293
-8.750 0.0228 0.02133 0.01576 -0.1929 0.7151 0.0296
-8.500 0.0547 0.02027 0.01456 -0.1952 0.7088 0.0301
-8.250 0.0862 0.01934 0.01346 -0.1971 0.7015 0.0306
-8.000 0.1174 0.01850 0.01244 -0.1987 0.6945 0.0310
-7.750 0.1485 0.01777 0.01157 -0.2001 0.6860 0.0313
-7.500 0.1789 0.01715 0.01080 -0.2012 0.6773 0.0315
-7.250 0.2096 0.01659 0.01020 -0.2022 0.6681 0.0318
-7.000 0.2398 0.01620 0.00972 -0.2030 0.6590 0.0321
-6.750 0.2706 0.01582 0.00930 -0.2040 0.6495 0.0325
-6.500 0.3009 0.01551 0.00889 -0.2047 0.6399 0.0328
-6.250 0.3315 0.01519 0.00850 -0.2055 0.6295 0.0332
-6.000 0.3618 0.01490 0.00813 -0.2062 0.6192 0.0337
-5.750 0.3922 0.01463 0.00777 -0.2070 0.6080 0.0342
-5.500 0.4225 0.01438 0.00743 -0.2076 0.5971 0.0347
-5.250 0.4522 0.01421 0.00713 -0.2082 0.5854 0.0353
-5.000 0.4825 0.01402 0.00685 -0.2088 0.5739 0.0358
-4.750 0.5127 0.01382 0.00660 -0.2095 0.5633 0.0365
-4.500 0.5427 0.01369 0.00640 -0.2101 0.5529 0.0370
-4.250 0.5725 0.01358 0.00622 -0.2107 0.5428 0.0377
-4.000 0.6021 0.01350 0.00606 -0.2112 0.5321 0.0384
-3.750 0.6319 0.01341 0.00589 -0.2117 0.5227 0.0392
-3.500 0.6611 0.01336 0.00575 -0.2121 0.5130 0.0400
-3.250 0.6911 0.01327 0.00560 -0.2126 0.5052 0.0408
-3.000 0.7207 0.01321 0.00549 -0.2131 0.4975 0.0419
-2.750 0.7496 0.01321 0.00543 -0.2134 0.4913 0.0432
-2.500 0.7792 0.01316 0.00535 -0.2138 0.4858 0.0448
-2.250 0.8084 0.01315 0.00528 -0.2142 0.4797 0.0462
-1.750 0.8660 0.01315 0.00520 -0.2147 0.4684 0.0500
-1.500 0.8947 0.01317 0.00517 -0.2149 0.4629 0.0522
-1.250 0.9228 0.01320 0.00516 -0.2151 0.4576 0.0553
-1.000 0.9507 0.01327 0.00518 -0.2152 0.4528 0.0591
-0.750 0.9794 0.01328 0.00518 -0.2154 0.4483 0.0647
-0.500 1.0075 0.01331 0.00521 -0.2155 0.4439 0.0746
-0.250 1.0406 0.01279 0.00518 -0.2174 0.4398 0.2907
0.000 1.0676 0.01289 0.00532 -0.2174 0.4362 0.3295
0.250 1.0951 0.01298 0.00544 -0.2174 0.4332 0.3525
0.500 1.1223 0.01308 0.00557 -0.2173 0.4301 0.3698
0.750 1.1489 0.01322 0.00572 -0.2171 0.4264 0.3828
1.000 1.1745 0.01340 0.00588 -0.2167 0.4221 0.3943
1.250 1.1992 0.01361 0.00606 -0.2162 0.4177 0.4048
1.500 1.2252 0.01376 0.00621 -0.2159 0.4147 0.4136
1.750 1.2511 0.01391 0.00639 -0.2156 0.4118 0.4234
2.000 1.2763 0.01409 0.00656 -0.2151 0.4086 0.4316
2.250 1.3006 0.01428 0.00676 -0.2145 0.4050 0.4386
2.500 1.3235 0.01453 0.00698 -0.2137 0.4010 0.4443
2.750 1.3456 0.01475 0.00718 -0.2127 0.3972 0.4493
3.000 1.3678 0.01493 0.00737 -0.2117 0.3933 0.4541
3.250 1.3887 0.01515 0.00762 -0.2106 0.3889 0.4593
3.500 1.4099 0.01544 0.00789 -0.2095 0.3847 0.4648
3.750 1.4305 0.01578 0.00820 -0.2084 0.3807 0.4698
4.000 1.4540 0.01601 0.00845 -0.2078 0.3772 0.4741
4.250 1.4764 0.01628 0.00875 -0.2070 0.3732 0.4785
4.500 1.4974 0.01662 0.00909 -0.2060 0.3686 0.4834
4.750 1.5168 0.01703 0.00949 -0.2048 0.3641 0.4885
5.000 1.5384 0.01735 0.00982 -0.2040 0.3597 0.4933
5.250 1.5590 0.01772 0.01020 -0.2030 0.3541 0.4973
5.500 1.5768 0.01823 0.01070 -0.2017 0.3480 0.5012
5.750 1.5964 0.01866 0.01115 -0.2006 0.3418 0.5056
6.000 1.6137 0.01922 0.01169 -0.1993 0.3334 0.5102
6.250 1.6302 0.01984 0.01228 -0.1978 0.3245 0.5144
6.500 1.6440 0.02061 0.01302 -0.1961 0.3127 0.5179
6.750 1.6555 0.02155 0.01391 -0.1941 0.2980 0.5213
7.000 1.6643 0.02269 0.01497 -0.1919 0.2824 0.5250
7.500 1.6829 0.02506 0.01724 -0.1879 0.2596 0.5327
8.000 1.7039 0.02739 0.01957 -0.1844 0.2469 0.5389
8.250 1.7153 0.02854 0.02074 -0.1829 0.2424 0.5425
8.500 1.7252 0.02983 0.02205 -0.1813 0.2384 0.5462
8.750 1.7351 0.03113 0.02336 -0.1798 0.2350 0.5496
9.000 1.7473 0.03228 0.02455 -0.1785 0.2329 0.5527
9.250 1.7593 0.03347 0.02579 -0.1773 0.2306 0.5558
9.500 1.7692 0.03484 0.02722 -0.1759 0.2282 0.5591
9.750 1.7788 0.03627 0.02869 -0.1746 0.2259 0.5624
10.000 1.7862 0.03792 0.03037 -0.1732 0.2234 0.5655
10.250 1.7931 0.03964 0.03212 -0.1717 0.2209 0.5685
10.500 1.7992 0.04148 0.03400 -0.1703 0.2185 0.5714
10.750 1.8103 0.04288 0.03549 -0.1694 0.2175 0.5745
11.000 1.8202 0.04443 0.03711 -0.1684 0.2164 0.5778
11.250 1.8298 0.04600 0.03876 -0.1674 0.2153 0.5811
11.500 1.8378 0.04777 0.04059 -0.1663 0.2138 0.5841
11.750 1.8452 0.04960 0.04248 -0.1653 0.2120 0.5873
12.000 1.8506 0.05167 0.04462 -0.1642 0.2100 0.5903
12.250 1.8551 0.05388 0.04688 -0.1632 0.2080 0.5934
12.500 1.8583 0.05624 0.04930 -0.1622 0.2060 0.5967
12.750 1.8603 0.05875 0.05187 -0.1611 0.2042 0.5999
13.000 1.8625 0.06124 0.05441 -0.1601 0.2024 0.6029
13.250 1.8690 0.06334 0.05660 -0.1594 0.2013 0.6060
13.500 1.8769 0.06528 0.05864 -0.1588 0.2002 0.6099
13.750 1.8829 0.06748 0.06093 -0.1582 0.1987 0.6142
14.000 1.8882 0.06974 0.06328 -0.1576 0.1968 0.6186
14.500 1.8929 0.07499 0.06869 -0.1564 0.1926 0.6272
14.750 1.8930 0.07792 0.07168 -0.1558 0.1908 0.6320
15.000 1.8929 0.08087 0.07470 -0.1552 0.1890 0.6375
15.250 1.8915 0.08402 0.07792 -0.1548 0.1871 0.6445
15.500 1.8958 0.08648 0.08049 -0.1544 0.1856 0.6552
15.750 1.9004 0.08891 0.08307 -0.1542 0.1840 0.6742
16.000 1.9031 0.09099 0.08551 -0.1535 0.1820 0.9586
16.250 1.9039 0.09387 0.08847 -0.1532 0.1798 1.0000
16.500 1.9043 0.09681 0.09146 -0.1530 0.1773 1.0000
16.750 1.9003 0.10036 0.09506 -0.1529 0.1744 1.0000
17.000 1.8987 0.10359 0.09832 -0.1528 0.1714 1.0000
17.250 1.8996 0.10651 0.10133 -0.1528 0.1672 1.0000
17.500 1.8938 0.11032 0.10517 -0.1529 0.1610 1.0000
17.750 1.8878 0.11421 0.10910 -0.1532 0.1542 1.0000
18.000 1.8738 0.11924 0.11411 -0.1537 0.1426 1.0000
18.250 1.8412 0.12701 0.12178 -0.1548 0.1231 1.0000
18.500 1.8104 0.13457 0.12929 -0.1563 0.1065 1.0000
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