GOE 233 (MVA CA4) AIRFOIL (goe233-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 233 (MVA CA4) AIRFOIL (goe233-il) Reynolds number: 500,000 Max Cl/Cd: 115.76 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe233-il-500000-n5.txt Download as CSV file: xf-goe233-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 233 (MVA CA4) 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1520 0.09185 0.08906 -0.0734 0.8745 0.0183
-9.250 -0.2717 0.04421 0.04087 -0.1199 0.8465 0.0212
-9.000 -0.2399 0.03641 0.03275 -0.1383 0.8388 0.0216
-8.750 -0.1943 0.03054 0.02654 -0.1549 0.8316 0.0221
-8.500 -0.1453 0.02627 0.02191 -0.1681 0.8256 0.0227
-8.250 -0.0952 0.02297 0.01825 -0.1793 0.8199 0.0234
-8.000 -0.0522 0.02074 0.01574 -0.1863 0.8141 0.0238
-7.750 -0.0206 0.01961 0.01451 -0.1884 0.8085 0.0242
-7.500 0.0126 0.01860 0.01342 -0.1907 0.8027 0.0245
-7.250 0.0460 0.01768 0.01239 -0.1930 0.7962 0.0249
-7.000 0.0789 0.01687 0.01145 -0.1949 0.7901 0.0253
-6.750 0.1116 0.01617 0.01065 -0.1967 0.7836 0.0259
-6.500 0.1438 0.01555 0.00992 -0.1981 0.7772 0.0264
-6.250 0.1756 0.01500 0.00927 -0.1993 0.7713 0.0268
-6.000 0.2072 0.01450 0.00868 -0.2004 0.7642 0.0271
-5.750 0.2384 0.01407 0.00815 -0.2014 0.7573 0.0274
-5.500 0.2698 0.01366 0.00767 -0.2024 0.7502 0.0277
-5.250 0.3009 0.01332 0.00723 -0.2032 0.7425 0.0279
-5.000 0.3326 0.01282 0.00670 -0.2043 0.7341 0.0284
-4.750 0.3642 0.01241 0.00621 -0.2053 0.7237 0.0290
-4.500 0.3957 0.01204 0.00577 -0.2063 0.7133 0.0296
-4.250 0.4269 0.01172 0.00534 -0.2072 0.7043 0.0300
-4.000 0.4582 0.01141 0.00496 -0.2080 0.6963 0.0305
-3.500 0.5196 0.01093 0.00431 -0.2093 0.6815 0.0315
-3.250 0.5498 0.01076 0.00404 -0.2098 0.6742 0.0320
-3.000 0.5800 0.01062 0.00382 -0.2102 0.6678 0.0324
-2.750 0.6101 0.01046 0.00359 -0.2107 0.6616 0.0332
-2.250 0.6698 0.01024 0.00322 -0.2113 0.6497 0.0360
-2.000 0.6993 0.01017 0.00310 -0.2116 0.6435 0.0377
-1.750 0.7288 0.01010 0.00299 -0.2118 0.6373 0.0429
-1.500 0.7586 0.00997 0.00290 -0.2122 0.6307 0.0741
-1.250 0.7878 0.00992 0.00283 -0.2124 0.6243 0.0861
-1.000 0.8177 0.00973 0.00274 -0.2129 0.6188 0.1384
-0.750 0.8469 0.00967 0.00270 -0.2131 0.6124 0.1588
-0.500 0.8759 0.00959 0.00267 -0.2133 0.6055 0.1951
-0.250 0.9048 0.00955 0.00274 -0.2135 0.5992 0.2489
0.000 0.9332 0.00961 0.00283 -0.2134 0.5930 0.2686
0.250 0.9613 0.00972 0.00290 -0.2133 0.5877 0.2790
0.500 0.9896 0.00980 0.00300 -0.2133 0.5827 0.2900
0.750 1.0177 0.00991 0.00313 -0.2131 0.5765 0.3001
1.000 1.0453 0.01006 0.00322 -0.2129 0.5699 0.3081
1.250 1.0734 0.01014 0.00332 -0.2128 0.5637 0.3115
1.500 1.1012 0.01025 0.00343 -0.2127 0.5565 0.3145
1.750 1.1288 0.01037 0.00353 -0.2125 0.5492 0.3180
2.000 1.1564 0.01048 0.00362 -0.2123 0.5406 0.3213
2.250 1.1837 0.01061 0.00371 -0.2121 0.5318 0.3242
2.500 1.2109 0.01074 0.00386 -0.2119 0.5228 0.3273
2.750 1.2380 0.01089 0.00401 -0.2116 0.5148 0.3306
3.000 1.2648 0.01105 0.00415 -0.2113 0.5046 0.3334
3.250 1.2914 0.01122 0.00430 -0.2110 0.4929 0.3361
3.500 1.3176 0.01142 0.00445 -0.2106 0.4823 0.3389
3.750 1.3435 0.01163 0.00463 -0.2102 0.4706 0.3413
4.000 1.3694 0.01183 0.00483 -0.2098 0.4588 0.3433
4.250 1.3950 0.01206 0.00504 -0.2093 0.4485 0.3451
4.500 1.4201 0.01231 0.00527 -0.2088 0.4372 0.3469
4.750 1.4456 0.01254 0.00550 -0.2083 0.4264 0.3488
5.000 1.4705 0.01280 0.00575 -0.2077 0.4166 0.3507
5.250 1.4947 0.01309 0.00602 -0.2070 0.4040 0.3527
5.500 1.5186 0.01342 0.00631 -0.2063 0.3888 0.3545
5.750 1.5411 0.01382 0.00664 -0.2054 0.3701 0.3561
6.000 1.5627 0.01428 0.00702 -0.2043 0.3449 0.3579
6.250 1.5812 0.01495 0.00753 -0.2028 0.3096 0.3598
6.500 1.5968 0.01581 0.00819 -0.2008 0.2729 0.3616
6.750 1.6134 0.01655 0.00881 -0.1990 0.2491 0.3635
7.000 1.6308 0.01720 0.00938 -0.1972 0.2335 0.3654
7.250 1.6485 0.01777 0.00993 -0.1955 0.2235 0.3673
7.500 1.6678 0.01820 0.01039 -0.1941 0.2168 0.3692
7.750 1.6836 0.01878 0.01097 -0.1921 0.2088 0.3709
8.000 1.6985 0.01923 0.01146 -0.1898 0.2029 0.3725
8.250 1.7128 0.01977 0.01204 -0.1875 0.1963 0.3743
8.500 1.7270 0.02041 0.01271 -0.1854 0.1892 0.3763
8.750 1.7414 0.02107 0.01338 -0.1833 0.1790 0.3784
9.000 1.7534 0.02189 0.01419 -0.1810 0.1650 0.3805
9.250 1.7607 0.02305 0.01523 -0.1782 0.1426 0.3823
9.500 1.7585 0.02491 0.01688 -0.1743 0.1078 0.3837
9.750 1.7544 0.02703 0.01884 -0.1705 0.0815 0.3850
10.000 1.7570 0.02877 0.02054 -0.1677 0.0676 0.3865
10.250 1.7610 0.03046 0.02222 -0.1651 0.0577 0.3879
10.500 1.7664 0.03211 0.02389 -0.1629 0.0509 0.3895
10.750 1.7732 0.03368 0.02552 -0.1609 0.0464 0.3913
11.000 1.7786 0.03543 0.02730 -0.1589 0.0426 0.3933
11.250 1.7854 0.03708 0.02902 -0.1571 0.0400 0.3955
11.500 1.7915 0.03883 0.03084 -0.1553 0.0377 0.3978
11.750 1.7957 0.04081 0.03286 -0.1535 0.0355 0.3999
12.000 1.8009 0.04274 0.03487 -0.1519 0.0338 0.4019
12.250 1.8061 0.04468 0.03690 -0.1503 0.0323 0.4037
12.500 1.8100 0.04681 0.03912 -0.1488 0.0308 0.4056
12.750 1.8123 0.04917 0.04155 -0.1474 0.0293 0.4076
13.000 1.8150 0.05156 0.04402 -0.1460 0.0280 0.4097
13.250 1.8191 0.05383 0.04640 -0.1448 0.0269 0.4121
13.500 1.8216 0.05633 0.04899 -0.1437 0.0255 0.4144
13.750 1.8225 0.05908 0.05180 -0.1426 0.0244 0.4168
14.000 1.8220 0.06206 0.05486 -0.1416 0.0233 0.4192
14.250 1.8245 0.06472 0.05764 -0.1407 0.0224 0.4221
14.500 1.8254 0.06759 0.06061 -0.1399 0.0213 0.4251
14.750 1.8249 0.07070 0.06380 -0.1392 0.0202 0.4281
15.000 1.8227 0.07408 0.06727 -0.1386 0.0192 0.4310
15.500 1.8203 0.08070 0.07410 -0.1376 0.0175 0.4371
15.750 1.8174 0.08428 0.07778 -0.1372 0.0167 0.4407
16.000 1.8135 0.08805 0.08164 -0.1370 0.0160 0.4446
16.250 1.8084 0.09204 0.08572 -0.1369 0.0154 0.4485
16.500 1.8050 0.09585 0.08965 -0.1369 0.0149 0.4534
16.750 1.8006 0.09985 0.09378 -0.1370 0.0144 0.4594
17.250 1.7897 0.10826 0.10241 -0.1377 0.0135 0.4760
17.500 1.7838 0.11261 0.10689 -0.1383 0.0131 0.4910
17.750 1.7776 0.11710 0.11153 -0.1391 0.0127 0.5421
18.000 1.7696 0.12135 0.11621 -0.1398 0.0124 1.0000
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