GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 242 (MVA PR.2) AIRFOIL (goe242-il) Reynolds number: 200,000 Max Cl/Cd: 80.76 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe242-il-200000-n5.txt Download as CSV file: xf-goe242-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 242 (MVA PR.2) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.0395 0.10574 0.10176 -0.0866 0.8449 0.0216
-10.500 -0.0348 0.10202 0.09802 -0.0883 0.8362 0.0217
-10.250 -0.0364 0.09643 0.09240 -0.0915 0.8288 0.0223
-10.000 -0.0258 0.09469 0.09064 -0.0919 0.8191 0.0232
-9.750 -0.0173 0.09217 0.08808 -0.0929 0.8099 0.0238
-9.500 -0.0160 0.08739 0.08327 -0.0955 0.8009 0.0234
-9.250 -0.0155 0.08240 0.07827 -0.0983 0.7919 0.0232
-9.000 -0.0137 0.07791 0.07375 -0.1008 0.7822 0.0233
-8.750 -0.0113 0.07351 0.06933 -0.1036 0.7717 0.0234
-8.500 -0.0087 0.06919 0.06498 -0.1065 0.7612 0.0238
-8.250 -0.0093 0.06369 0.05946 -0.1106 0.7503 0.0245
-8.000 -0.0454 0.04383 0.03927 -0.1373 0.7414 0.0241
-7.750 -0.0100 0.03562 0.03048 -0.1589 0.7289 0.0252
-7.500 0.0382 0.02984 0.02386 -0.1742 0.7167 0.0265
-7.250 0.0796 0.02677 0.02015 -0.1816 0.7043 0.0280
-7.000 0.1096 0.02559 0.01887 -0.1835 0.6929 0.0291
-6.750 0.1423 0.02433 0.01735 -0.1859 0.6824 0.0303
-6.500 0.1764 0.02296 0.01565 -0.1884 0.6724 0.0314
-6.250 0.2104 0.02196 0.01430 -0.1905 0.6636 0.0329
-6.000 0.2433 0.02100 0.01304 -0.1923 0.6552 0.0342
-5.750 0.2733 0.02003 0.01200 -0.1932 0.6479 0.0351
-5.500 0.3039 0.01934 0.01121 -0.1941 0.6409 0.0360
-5.250 0.3347 0.01883 0.01057 -0.1951 0.6351 0.0375
-5.000 0.3659 0.01835 0.01001 -0.1960 0.6295 0.0390
-4.750 0.3971 0.01791 0.00947 -0.1969 0.6244 0.0399
-4.500 0.4286 0.01755 0.00900 -0.1979 0.6201 0.0406
-4.250 0.4607 0.01723 0.00861 -0.1990 0.6158 0.0414
-4.000 0.4955 0.01670 0.00809 -0.2011 0.6114 0.0433
-3.750 0.5299 0.01638 0.00770 -0.2029 0.6075 0.0450
-3.500 0.5639 0.01615 0.00734 -0.2046 0.6040 0.0463
-3.250 0.5974 0.01596 0.00703 -0.2061 0.6004 0.0478
-3.000 0.6302 0.01580 0.00679 -0.2074 0.5965 0.0495
-2.750 0.6629 0.01567 0.00657 -0.2086 0.5930 0.0523
-2.500 0.6954 0.01556 0.00641 -0.2098 0.5900 0.0586
-2.250 0.7346 0.01496 0.00616 -0.2132 0.5872 0.1917
-2.000 0.7704 0.01460 0.00628 -0.2156 0.5846 0.3510
-1.750 0.7996 0.01477 0.00649 -0.2158 0.5818 0.3942
-1.500 0.8285 0.01497 0.00664 -0.2160 0.5791 0.4144
-1.250 0.8571 0.01521 0.00684 -0.2160 0.5763 0.4315
-1.000 0.8854 0.01547 0.00704 -0.2160 0.5736 0.4446
-0.750 0.9146 0.01566 0.00712 -0.2163 0.5711 0.4528
-0.250 0.9709 0.01621 0.00761 -0.2163 0.5666 0.4730
0.000 0.9984 0.01642 0.00787 -0.2162 0.5642 0.4780
0.250 1.0272 0.01656 0.00799 -0.2165 0.5616 0.4814
0.500 1.0560 0.01667 0.00804 -0.2168 0.5580 0.4852
0.750 1.0851 0.01678 0.00802 -0.2172 0.5538 0.4886
1.000 1.1126 0.01688 0.00813 -0.2172 0.5488 0.4904
1.250 1.1395 0.01699 0.00826 -0.2171 0.5433 0.4931
1.500 1.1669 0.01711 0.00836 -0.2171 0.5385 0.4968
1.750 1.1947 0.01727 0.00844 -0.2172 0.5342 0.5011
2.000 1.2224 0.01738 0.00856 -0.2173 0.5296 0.5048
2.250 1.2496 0.01750 0.00872 -0.2174 0.5257 0.5067
2.500 1.2769 0.01763 0.00885 -0.2174 0.5223 0.5085
2.750 1.3044 0.01779 0.00899 -0.2175 0.5194 0.5105
3.000 1.3315 0.01795 0.00920 -0.2175 0.5162 0.5128
3.250 1.3582 0.01810 0.00941 -0.2175 0.5125 0.5153
3.500 1.3849 0.01825 0.00959 -0.2175 0.5085 0.5183
3.750 1.4118 0.01842 0.00973 -0.2175 0.5047 0.5216
4.000 1.4379 0.01859 0.00993 -0.2174 0.5009 0.5238
4.250 1.4632 0.01876 0.01023 -0.2171 0.4961 0.5261
4.500 1.4885 0.01894 0.01047 -0.2168 0.4915 0.5285
4.750 1.5140 0.01912 0.01066 -0.2166 0.4873 0.5313
5.000 1.5389 0.01933 0.01095 -0.2163 0.4826 0.5343
5.250 1.5632 0.01954 0.01123 -0.2159 0.4771 0.5375
5.500 1.5871 0.01974 0.01147 -0.2154 0.4719 0.5401
5.750 1.6102 0.01997 0.01181 -0.2147 0.4660 0.5429
6.000 1.6324 0.02022 0.01215 -0.2140 0.4590 0.5461
6.250 1.6540 0.02048 0.01246 -0.2131 0.4519 0.5496
6.500 1.6745 0.02077 0.01283 -0.2120 0.4429 0.5531
6.750 1.6938 0.02109 0.01323 -0.2108 0.4335 0.5560
7.000 1.7106 0.02147 0.01365 -0.2091 0.4222 0.5587
7.250 1.7244 0.02194 0.01415 -0.2069 0.4072 0.5617
7.500 1.7308 0.02255 0.01474 -0.2035 0.3896 0.5649
7.750 1.7335 0.02348 0.01559 -0.1997 0.3696 0.5684
8.000 1.7338 0.02477 0.01678 -0.1959 0.3501 0.5717
8.250 1.7330 0.02628 0.01822 -0.1923 0.3330 0.5743
8.500 1.7327 0.02795 0.01983 -0.1891 0.3178 0.5773
8.750 1.7335 0.02967 0.02153 -0.1862 0.3042 0.5806
9.000 1.7360 0.03141 0.02326 -0.1837 0.2929 0.5841
9.250 1.7373 0.03331 0.02516 -0.1813 0.2835 0.5875
9.500 1.7420 0.03502 0.02694 -0.1794 0.2744 0.5905
9.750 1.7444 0.03697 0.02893 -0.1773 0.2672 0.5939
10.000 1.7486 0.03884 0.03088 -0.1755 0.2591 0.5980
10.250 1.7487 0.04113 0.03319 -0.1736 0.2513 0.6023
10.500 1.7503 0.04335 0.03547 -0.1719 0.2424 0.6060
10.750 1.7493 0.04587 0.03804 -0.1701 0.2344 0.6098
11.000 1.7491 0.04841 0.04064 -0.1686 0.2258 0.6142
11.250 1.7484 0.05110 0.04339 -0.1672 0.2179 0.6187
11.500 1.7465 0.05400 0.04635 -0.1659 0.2090 0.6225
11.750 1.7455 0.05691 0.04932 -0.1647 0.1995 0.6268
12.000 1.7414 0.06024 0.05268 -0.1636 0.1886 0.6315
12.250 1.7359 0.06383 0.05628 -0.1626 0.1742 0.6362
12.500 1.7213 0.06857 0.06094 -0.1615 0.1485 0.6399
12.750 1.6921 0.07521 0.06735 -0.1602 0.1038 0.6423
13.000 1.6663 0.08152 0.07350 -0.1592 0.0801 0.6452
13.250 1.6517 0.08653 0.07851 -0.1585 0.0675 0.6496
13.500 1.6440 0.09077 0.08281 -0.1580 0.0579 0.6550
13.750 1.6382 0.09482 0.08695 -0.1578 0.0486 0.6613
14.250 1.6101 0.10547 0.09759 -0.1578 0.0204 0.6723
14.500 1.6020 0.11013 0.10236 -0.1581 0.0185 0.6800
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