GOE 234 (MVA CA5) AIRFOIL (goe234-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 234 (MVA CA5) AIRFOIL (goe234-il) Reynolds number: 200,000 Max Cl/Cd: 79.4 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe234-il-200000-n5.txt Download as CSV file: xf-goe234-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 234 (MVA CA5) 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.0469 0.10181 0.09780 -0.0963 0.9152 0.0334
-10.250 -0.0433 0.09775 0.09371 -0.0982 0.9087 0.0336
-9.750 -0.0404 0.08896 0.08489 -0.1026 0.8938 0.0349
-9.500 -0.0272 0.08763 0.08355 -0.1030 0.8864 0.0356
-9.250 -0.0187 0.08502 0.08091 -0.1041 0.8799 0.0364
-9.000 -0.0145 0.08126 0.07713 -0.1061 0.8733 0.0368
-8.500 -0.0921 0.05156 0.04716 -0.1324 0.8539 0.0384
-8.250 -0.0484 0.03419 0.02881 -0.1758 0.8464 0.0397
-8.000 0.0006 0.03017 0.02440 -0.1882 0.8424 0.0405
-7.750 0.0358 0.02867 0.02282 -0.1925 0.8370 0.0414
-7.500 0.0743 0.02712 0.02113 -0.1975 0.8322 0.0425
-7.250 0.1141 0.02556 0.01935 -0.2025 0.8280 0.0438
-7.000 0.1517 0.02423 0.01782 -0.2064 0.8235 0.0449
-6.750 0.1873 0.02318 0.01659 -0.2093 0.8181 0.0459
-6.500 0.2210 0.02240 0.01566 -0.2112 0.8132 0.0468
-6.250 0.2501 0.02199 0.01524 -0.2115 0.8088 0.0480
-6.000 0.2817 0.02153 0.01477 -0.2128 0.8033 0.0494
-5.750 0.3133 0.02111 0.01431 -0.2139 0.7977 0.0510
-5.500 0.3442 0.02081 0.01393 -0.2146 0.7928 0.0524
-5.250 0.3751 0.02056 0.01359 -0.2152 0.7881 0.0538
-5.000 0.4036 0.02050 0.01358 -0.2152 0.7817 0.0553
-4.750 0.4348 0.02029 0.01339 -0.2160 0.7760 0.0575
-4.500 0.4669 0.02009 0.01312 -0.2171 0.7714 0.0603
-4.250 0.4984 0.01992 0.01292 -0.2181 0.7652 0.0629
-4.000 0.5311 0.01973 0.01275 -0.2193 0.7589 0.0662
-3.750 0.5666 0.01930 0.01222 -0.2215 0.7537 0.0706
-3.500 0.6054 0.01859 0.01146 -0.2250 0.7473 0.0774
-3.250 0.6481 0.01753 0.01033 -0.2297 0.7411 0.0911
-3.000 0.6914 0.01641 0.00969 -0.2348 0.7357 0.2121
-2.750 0.7184 0.01670 0.01002 -0.2343 0.7285 0.2453
-2.500 0.7564 0.01579 0.00883 -0.2375 0.7219 0.2688
-2.250 0.7803 0.01646 0.00953 -0.2358 0.7162 0.2737
-2.000 0.8117 0.01631 0.00925 -0.2368 0.7088 0.2849
-1.750 0.8365 0.01683 0.00977 -0.2354 0.7023 0.2873
-1.250 0.8954 0.01689 0.00966 -0.2360 0.6886 0.3000
-1.000 0.9193 0.01746 0.01025 -0.2345 0.6823 0.3019
-0.750 0.9435 0.01793 0.01076 -0.2332 0.6742 0.3047
-0.500 0.9786 0.01744 0.01000 -0.2353 0.6666 0.3140
-0.250 1.0061 0.01751 0.01005 -0.2351 0.6577 0.3154
0.000 1.0332 0.01762 0.01008 -0.2348 0.6492 0.3165
0.250 1.0601 0.01772 0.01016 -0.2345 0.6392 0.3179
0.500 1.0871 0.01781 0.01016 -0.2342 0.6287 0.3195
0.750 1.1141 0.01789 0.01016 -0.2340 0.6172 0.3216
1.000 1.1424 0.01789 0.01009 -0.2342 0.6074 0.3247
1.250 1.1755 0.01753 0.00950 -0.2358 0.5996 0.3303
1.500 1.2028 0.01760 0.00955 -0.2357 0.5928 0.3311
1.750 1.2299 0.01768 0.00963 -0.2356 0.5857 0.3319
2.000 1.2570 0.01779 0.00969 -0.2354 0.5792 0.3329
2.250 1.2840 0.01787 0.00980 -0.2353 0.5721 0.3340
2.500 1.3107 0.01797 0.00988 -0.2352 0.5649 0.3353
2.750 1.3375 0.01808 0.00996 -0.2350 0.5581 0.3368
3.000 1.3640 0.01818 0.01006 -0.2348 0.5504 0.3387
3.500 1.4171 0.01836 0.01018 -0.2346 0.5349 0.3440
3.750 1.4432 0.01847 0.01020 -0.2344 0.5265 0.3462
4.000 1.4676 0.01865 0.01043 -0.2338 0.5175 0.3472
4.250 1.4911 0.01889 0.01065 -0.2330 0.5081 0.3482
4.500 1.5146 0.01910 0.01090 -0.2322 0.4976 0.3495
4.750 1.5371 0.01936 0.01116 -0.2312 0.4873 0.3508
5.000 1.5589 0.01964 0.01145 -0.2302 0.4759 0.3524
5.250 1.5803 0.01993 0.01174 -0.2290 0.4643 0.3541
5.500 1.6002 0.02028 0.01207 -0.2276 0.4521 0.3563
5.750 1.6184 0.02068 0.01243 -0.2260 0.4386 0.3588
6.000 1.6354 0.02112 0.01280 -0.2241 0.4230 0.3613
6.250 1.6490 0.02166 0.01332 -0.2216 0.4064 0.3626
6.500 1.6587 0.02230 0.01391 -0.2185 0.3899 0.3636
6.750 1.6642 0.02303 0.01462 -0.2146 0.3739 0.3646
7.000 1.6729 0.02388 0.01544 -0.2115 0.3582 0.3658
7.250 1.6826 0.02479 0.01631 -0.2088 0.3443 0.3672
7.500 1.6924 0.02574 0.01724 -0.2062 0.3325 0.3687
7.750 1.7019 0.02676 0.01823 -0.2036 0.3219 0.3704
8.000 1.7136 0.02769 0.01918 -0.2014 0.3128 0.3723
8.500 1.7353 0.02976 0.02126 -0.1971 0.2973 0.3767
8.750 1.7456 0.03087 0.02241 -0.1949 0.2906 0.3782
9.000 1.7555 0.03204 0.02363 -0.1928 0.2841 0.3796
9.250 1.7657 0.03322 0.02486 -0.1908 0.2765 0.3811
9.500 1.7724 0.03468 0.02632 -0.1885 0.2698 0.3826
9.750 1.7842 0.03581 0.02754 -0.1868 0.2634 0.3843
10.000 1.7928 0.03720 0.02898 -0.1849 0.2571 0.3861
10.250 1.8003 0.03872 0.03053 -0.1829 0.2520 0.3879
10.500 1.8118 0.03995 0.03186 -0.1814 0.2468 0.3899
10.750 1.8199 0.04147 0.03343 -0.1796 0.2408 0.3919
11.000 1.8245 0.04329 0.03527 -0.1775 0.2354 0.3935
11.250 1.8338 0.04475 0.03687 -0.1760 0.2286 0.3952
11.500 1.8387 0.04662 0.03881 -0.1742 0.2217 0.3969
11.750 1.8439 0.04852 0.04079 -0.1725 0.2161 0.3988
12.000 1.8509 0.05029 0.04267 -0.1710 0.2088 0.4008
12.250 1.8520 0.05270 0.04510 -0.1692 0.2014 0.4025
12.500 1.8576 0.05474 0.04724 -0.1678 0.1908 0.4045
12.750 1.8583 0.05734 0.04989 -0.1663 0.1760 0.4062
13.000 1.8449 0.06161 0.05400 -0.1644 0.1414 0.4072
13.250 1.8198 0.06739 0.05952 -0.1624 0.1110 0.4077
13.500 1.8044 0.07221 0.06429 -0.1608 0.0939 0.4085
13.750 1.7914 0.07689 0.06896 -0.1596 0.0758 0.4093
14.000 1.7708 0.08270 0.07468 -0.1586 0.0536 0.4099
14.250 1.7570 0.08778 0.07978 -0.1580 0.0460 0.4108
14.500 1.7477 0.09238 0.08446 -0.1576 0.0427 0.4119
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