GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Reynolds number: 200,000 Max Cl/Cd: 69.39 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe243-il-200000-n5.txt Download as CSV file: xf-goe243-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 243 (MVA PR.3) 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
------ -------- --------- --------- -------- -------- --------
-10.000 0.1235 0.09441 0.08982 -0.1144 0.8197 0.0434
-9.500 0.1284 0.08525 0.08059 -0.1185 0.8078 0.0387
-9.250 0.1347 0.08200 0.07728 -0.1201 0.8025 0.0386
-9.000 0.1349 0.07723 0.07251 -0.1230 0.7965 0.0387
-8.750 0.1374 0.07307 0.06833 -0.1255 0.7903 0.0386
-8.500 0.1411 0.06925 0.06448 -0.1277 0.7846 0.0384
-8.250 0.1365 0.06333 0.05849 -0.1316 0.7795 0.0380
-8.000 0.0669 0.04580 0.04064 -0.1507 0.7709 0.0369
-7.750 0.0750 0.03744 0.03180 -0.1684 0.7639 0.0367
-7.500 0.1106 0.03252 0.02640 -0.1816 0.7582 0.0369
-7.250 0.1482 0.02942 0.02297 -0.1901 0.7506 0.0372
-7.000 0.1856 0.02719 0.02040 -0.1958 0.7437 0.0376
-6.750 0.2217 0.02552 0.01841 -0.1996 0.7382 0.0380
-6.500 0.2546 0.02425 0.01694 -0.2022 0.7319 0.0384
-6.250 0.2863 0.02331 0.01588 -0.2040 0.7258 0.0390
-6.000 0.3175 0.02265 0.01517 -0.2053 0.7205 0.0396
-5.750 0.3491 0.02202 0.01447 -0.2066 0.7154 0.0403
-5.500 0.3793 0.02142 0.01383 -0.2076 0.7091 0.0409
-5.250 0.4098 0.02083 0.01316 -0.2084 0.7032 0.0414
-5.000 0.4408 0.02028 0.01251 -0.2092 0.6979 0.0420
-4.750 0.4708 0.01982 0.01201 -0.2098 0.6919 0.0426
-4.500 0.5010 0.01942 0.01156 -0.2104 0.6855 0.0432
-4.250 0.5321 0.01903 0.01116 -0.2112 0.6797 0.0439
-4.000 0.5643 0.01868 0.01080 -0.2124 0.6740 0.0448
-3.750 0.5961 0.01836 0.01049 -0.2135 0.6670 0.0458
-3.500 0.6291 0.01806 0.01013 -0.2148 0.6604 0.0472
-3.250 0.6631 0.01776 0.00977 -0.2164 0.6546 0.0490
-3.000 0.6965 0.01748 0.00952 -0.2180 0.6473 0.0511
-2.750 0.7306 0.01722 0.00917 -0.2196 0.6401 0.0534
-2.500 0.7652 0.01695 0.00882 -0.2214 0.6333 0.0559
-2.250 0.7981 0.01674 0.00856 -0.2228 0.6256 0.0596
-2.000 0.8313 0.01654 0.00828 -0.2241 0.6184 0.0653
-1.750 0.8637 0.01635 0.00806 -0.2253 0.6106 0.0761
-1.500 0.8960 0.01613 0.00781 -0.2265 0.6012 0.0989
-1.250 0.9340 0.01548 0.00757 -0.2296 0.5918 0.2790
-1.000 0.9619 0.01558 0.00767 -0.2296 0.5819 0.3068
-0.750 0.9894 0.01573 0.00774 -0.2295 0.5732 0.3257
-0.500 1.0162 0.01592 0.00791 -0.2292 0.5634 0.3464
-0.250 1.0425 0.01616 0.00802 -0.2288 0.5540 0.3630
0.000 1.0678 0.01634 0.00824 -0.2282 0.5430 0.3722
0.250 1.0930 0.01657 0.00835 -0.2277 0.5325 0.3806
0.500 1.1183 0.01677 0.00846 -0.2272 0.5213 0.3874
0.750 1.1428 0.01698 0.00863 -0.2265 0.5119 0.3921
1.000 1.1675 0.01719 0.00879 -0.2259 0.5022 0.3963
1.250 1.1915 0.01743 0.00894 -0.2253 0.4934 0.4007
1.500 1.2158 0.01767 0.00911 -0.2246 0.4843 0.4054
1.750 1.2386 0.01796 0.00929 -0.2238 0.4762 0.4098
2.000 1.2620 0.01820 0.00956 -0.2230 0.4682 0.4142
2.250 1.2841 0.01851 0.00983 -0.2220 0.4606 0.4191
2.500 1.3062 0.01883 0.01010 -0.2210 0.4538 0.4247
2.750 1.3282 0.01914 0.01036 -0.2201 0.4464 0.4311
3.000 1.3477 0.01952 0.01072 -0.2187 0.4394 0.4365
3.250 1.3669 0.01987 0.01108 -0.2172 0.4333 0.4426
3.500 1.3855 0.02023 0.01143 -0.2157 0.4271 0.4494
3.750 1.4039 0.02066 0.01182 -0.2142 0.4209 0.4559
4.000 1.4229 0.02112 0.01228 -0.2128 0.4155 0.4616
4.250 1.4429 0.02154 0.01274 -0.2116 0.4100 0.4684
4.500 1.4619 0.02202 0.01319 -0.2104 0.4044 0.4761
4.750 1.4790 0.02259 0.01375 -0.2088 0.3992 0.4822
5.000 1.4973 0.02310 0.01430 -0.2074 0.3934 0.4894
5.250 1.5144 0.02367 0.01487 -0.2060 0.3868 0.4979
5.500 1.5299 0.02434 0.01553 -0.2043 0.3810 0.5039
5.750 1.5467 0.02496 0.01618 -0.2028 0.3761 0.5105
6.000 1.5643 0.02556 0.01681 -0.2016 0.3709 0.5182
6.250 1.5793 0.02629 0.01755 -0.2000 0.3648 0.5241
6.500 1.5921 0.02715 0.01839 -0.1981 0.3591 0.5298
6.750 1.6088 0.02783 0.01913 -0.1968 0.3538 0.5372
7.000 1.6236 0.02864 0.01996 -0.1953 0.3483 0.5438
7.250 1.6360 0.02957 0.02091 -0.1936 0.3429 0.5490
7.500 1.6496 0.03048 0.02186 -0.1921 0.3378 0.5551
7.750 1.6638 0.03140 0.02280 -0.1907 0.3318 0.5617
8.000 1.6746 0.03251 0.02395 -0.1890 0.3257 0.5659
8.250 1.6854 0.03366 0.02512 -0.1873 0.3199 0.5709
8.500 1.6970 0.03480 0.02632 -0.1859 0.3131 0.5769
8.750 1.7051 0.03622 0.02773 -0.1841 0.3061 0.5824
9.000 1.7146 0.03755 0.02911 -0.1826 0.2991 0.5865
9.250 1.7215 0.03911 0.03070 -0.1808 0.2908 0.5911
9.500 1.7278 0.04078 0.03238 -0.1792 0.2827 0.5963
9.750 1.7322 0.04268 0.03429 -0.1775 0.2732 0.6012
10.000 1.7365 0.04462 0.03625 -0.1759 0.2636 0.6048
10.250 1.7370 0.04696 0.03860 -0.1741 0.2536 0.6087
10.500 1.7385 0.04931 0.04095 -0.1725 0.2429 0.6132
10.750 1.7385 0.05187 0.04350 -0.1710 0.2332 0.6176
11.250 1.7362 0.05740 0.04905 -0.1681 0.2167 0.6244
11.500 1.7338 0.06038 0.05204 -0.1668 0.2104 0.6280
11.750 1.7345 0.06309 0.05479 -0.1656 0.2056 0.6320
12.000 1.7349 0.06589 0.05762 -0.1646 0.2014 0.6361
12.250 1.7342 0.06885 0.06061 -0.1636 0.1978 0.6396
12.500 1.7325 0.07192 0.06372 -0.1626 0.1948 0.6426
12.750 1.7358 0.07444 0.06631 -0.1618 0.1924 0.6464
13.000 1.7380 0.07712 0.06905 -0.1610 0.1902 0.6503
13.250 1.7407 0.07976 0.07174 -0.1603 0.1881 0.6544
13.500 1.7428 0.08247 0.07450 -0.1597 0.1863 0.6581
13.750 1.7453 0.08512 0.07721 -0.1590 0.1847 0.6615
14.000 1.7482 0.08769 0.07982 -0.1584 0.1834 0.6654
14.250 1.7515 0.09022 0.08238 -0.1579 0.1821 0.6695
14.500 1.7567 0.09247 0.08464 -0.1573 0.1809 0.6738
14.750 1.7638 0.09451 0.08676 -0.1568 0.1800 0.6779
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