GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Reynolds number: 200,000 Max Cl/Cd: 70.39 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe243-il-200000.txt Download as CSV file: xf-goe243-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.1631 0.10714 0.10317 -0.1187 0.9024 0.0675
-10.250 0.1704 0.10460 0.10059 -0.1194 0.8975 0.0693
-10.000 0.1491 0.10073 0.09675 -0.1254 0.8874 0.0719
-9.750 0.1691 0.09844 0.09443 -0.1236 0.8824 0.0724
-9.500 0.1857 0.09649 0.09246 -0.1225 0.8774 0.0733
-9.250 0.1979 0.09456 0.09054 -0.1226 0.8698 0.0747
-9.000 0.2053 0.09216 0.08812 -0.1234 0.8637 0.0772
-8.750 0.1912 0.08764 0.08358 -0.1288 0.8568 0.0802
-8.500 0.2091 0.08594 0.08188 -0.1273 0.8495 0.0809
-8.250 0.2237 0.08406 0.07995 -0.1266 0.8433 0.0821
-8.000 0.2346 0.08202 0.07790 -0.1268 0.8365 0.0839
-7.750 0.2130 0.07632 0.07222 -0.1348 0.8274 0.0892
-7.500 0.2345 0.07493 0.07078 -0.1326 0.8224 0.0899
-7.250 0.2513 0.07357 0.06941 -0.1317 0.8162 0.0911
-7.000 0.2187 0.06647 0.06235 -0.1431 0.8067 0.0990
-6.750 0.2435 0.06600 0.06184 -0.1391 0.8023 0.0997
-6.500 0.2644 0.06519 0.06101 -0.1371 0.7969 0.1008
-6.250 0.2785 0.06404 0.05988 -0.1363 0.7898 0.1027
-6.000 0.2752 0.05788 0.05371 -0.1461 0.7834 0.1116
-5.750 0.3590 0.02967 0.02355 -0.2127 0.7777 0.0735
-5.500 0.3927 0.02767 0.02128 -0.2153 0.7707 0.0691
-5.250 0.4304 0.02565 0.01891 -0.2181 0.7652 0.0666
-5.000 0.4693 0.02410 0.01696 -0.2207 0.7607 0.0655
-4.750 0.5002 0.02320 0.01594 -0.2215 0.7550 0.0655
-4.500 0.5290 0.02243 0.01514 -0.2218 0.7481 0.0660
-4.250 0.5606 0.02165 0.01429 -0.2223 0.7426 0.0668
-4.000 0.5939 0.02103 0.01357 -0.2232 0.7381 0.0685
-3.750 0.6213 0.02066 0.01319 -0.2232 0.7307 0.0703
-3.500 0.6525 0.02021 0.01263 -0.2236 0.7243 0.0717
-3.250 0.6831 0.01950 0.01199 -0.2238 0.7191 0.0733
-3.000 0.7115 0.01919 0.01175 -0.2239 0.7121 0.0755
-2.750 0.7418 0.01886 0.01142 -0.2242 0.7051 0.0783
-2.500 0.7760 0.01839 0.01096 -0.2254 0.6994 0.0822
-2.250 0.8083 0.01816 0.01073 -0.2264 0.6922 0.0886
-2.000 0.8451 0.01763 0.01020 -0.2287 0.6844 0.0995
-1.750 0.8970 0.01628 0.00928 -0.2351 0.6781 0.3217
-1.500 0.9227 0.01670 0.00976 -0.2343 0.6699 0.3572
-1.250 0.9499 0.01694 0.00997 -0.2337 0.6622 0.3742
-1.000 0.9793 0.01710 0.00998 -0.2337 0.6546 0.3877
-0.750 1.0022 0.01738 0.01037 -0.2322 0.6447 0.3994
-0.500 1.0304 0.01762 0.01049 -0.2317 0.6368 0.4134
-0.250 1.0519 0.01794 0.01092 -0.2301 0.6262 0.4227
0.000 1.0826 0.01796 0.01073 -0.2305 0.6179 0.4316
0.250 1.1049 0.01818 0.01104 -0.2291 0.6082 0.4368
0.500 1.1320 0.01828 0.01106 -0.2287 0.5996 0.4420
0.750 1.1594 0.01833 0.01104 -0.2287 0.5900 0.4468
1.000 1.1887 0.01831 0.01083 -0.2292 0.5806 0.4521
1.250 1.2145 0.01838 0.01088 -0.2288 0.5710 0.4559
1.500 1.2394 0.01853 0.01099 -0.2281 0.5616 0.4598
1.750 1.2647 0.01874 0.01114 -0.2276 0.5528 0.4649
2.000 1.2905 0.01889 0.01122 -0.2273 0.5436 0.4715
2.250 1.3175 0.01906 0.01125 -0.2272 0.5354 0.4773
2.500 1.3395 0.01930 0.01154 -0.2261 0.5262 0.4814
3.000 1.3882 0.01982 0.01195 -0.2249 0.5102 0.4942
3.250 1.4127 0.02007 0.01213 -0.2243 0.5029 0.5003
3.500 1.4355 0.02042 0.01247 -0.2234 0.4959 0.5054
3.750 1.4565 0.02075 0.01282 -0.2222 0.4883 0.5126
4.000 1.4817 0.02106 0.01300 -0.2219 0.4817 0.5212
4.250 1.5020 0.02144 0.01343 -0.2205 0.4752 0.5261
4.500 1.5218 0.02181 0.01383 -0.2192 0.4685 0.5329
4.750 1.5466 0.02216 0.01405 -0.2188 0.4626 0.5422
5.000 1.5664 0.02257 0.01450 -0.2175 0.4570 0.5472
5.250 1.5830 0.02298 0.01497 -0.2156 0.4505 0.5544
5.500 1.6034 0.02336 0.01527 -0.2145 0.4443 0.5635
5.750 1.6212 0.02381 0.01573 -0.2128 0.4388 0.5692
6.000 1.6332 0.02427 0.01627 -0.2103 0.4330 0.5770
6.250 1.6507 0.02473 0.01672 -0.2087 0.4274 0.5846
6.500 1.6740 0.02517 0.01707 -0.2081 0.4222 0.5912
6.750 1.6868 0.02577 0.01777 -0.2060 0.4170 0.6000
7.000 1.7000 0.02634 0.01842 -0.2039 0.4115 0.6059
7.250 1.7169 0.02689 0.01895 -0.2023 0.4062 0.6135
7.500 1.7352 0.02747 0.01949 -0.2012 0.4009 0.6220
7.750 1.7439 0.02822 0.02038 -0.1986 0.3953 0.6277
8.000 1.7562 0.02894 0.02113 -0.1966 0.3895 0.6353
8.250 1.7750 0.02950 0.02159 -0.1956 0.3839 0.6423
8.500 1.7802 0.03050 0.02277 -0.1928 0.3781 0.6485
8.750 1.7894 0.03146 0.02377 -0.1907 0.3719 0.6565
9.000 1.8025 0.03223 0.02449 -0.1890 0.3661 0.6623
9.250 1.8081 0.03342 0.02582 -0.1866 0.3597 0.6686
9.500 1.8144 0.03466 0.02712 -0.1845 0.3526 0.6756
9.750 1.8230 0.03577 0.02819 -0.1825 0.3460 0.6811
10.000 1.8248 0.03740 0.02998 -0.1802 0.3378 0.6873
10.250 1.8293 0.03892 0.03144 -0.1782 0.3298 0.6934
10.500 1.8295 0.04083 0.03348 -0.1760 0.3202 0.6984
10.750 1.8293 0.04282 0.03541 -0.1738 0.3108 0.7041
11.000 1.8271 0.04524 0.03791 -0.1718 0.2992 0.7097
11.250 1.8242 0.04772 0.04041 -0.1698 0.2881 0.7141
11.500 1.8200 0.05043 0.04303 -0.1678 0.2776 0.7190
11.750 1.8185 0.05311 0.04576 -0.1663 0.2671 0.7245
12.000 1.8167 0.05577 0.04835 -0.1647 0.2592 0.7292
12.250 1.8180 0.05821 0.05083 -0.1634 0.2518 0.7345
12.500 1.8190 0.06066 0.05320 -0.1620 0.2463 0.7400
12.750 1.8242 0.06276 0.05534 -0.1609 0.2416 0.7454
13.000 1.8291 0.06489 0.05753 -0.1599 0.2375 0.7511
13.250 1.8349 0.06691 0.05953 -0.1589 0.2340 0.7574
13.500 1.8438 0.06847 0.06104 -0.1579 0.2311 0.7635
13.750 1.8543 0.06992 0.06249 -0.1569 0.2285 0.7705
14.000 1.8617 0.07185 0.06451 -0.1562 0.2263 0.7773
14.250 1.8698 0.07366 0.06641 -0.1554 0.2242 0.7848
14.500 1.8785 0.07539 0.06822 -0.1547 0.2222 0.7928
14.750 1.8876 0.07704 0.06993 -0.1539 0.2203 0.8024
15.000 1.8980 0.07851 0.07145 -0.1533 0.2185 0.8147
15.500 1.9269 0.07986 0.07285 -0.1515 0.2154 1.0000
15.750 1.9440 0.08060 0.07360 -0.1508 0.2142 1.0000
16.000 1.9496 0.08283 0.07595 -0.1503 0.2132 1.0000
16.250 1.9551 0.08504 0.07829 -0.1498 0.2123 1.0000
16.500 1.9607 0.08724 0.08061 -0.1493 0.2113 1.0000
16.750 1.9660 0.08946 0.08294 -0.1489 0.2103 1.0000
17.000 1.9706 0.09177 0.08536 -0.1485 0.2094 1.0000
17.250 1.9749 0.09412 0.08782 -0.1481 0.2085 1.0000
17.500 1.9791 0.09648 0.09030 -0.1478 0.2076 1.0000
17.750 1.9822 0.09898 0.09291 -0.1476 0.2068 1.0000
18.000 1.9850 0.10152 0.09556 -0.1474 0.2060 1.0000
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