GOE 229 (MVA H.39) AIRFOIL (goe229-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 229 (MVA H.39) AIRFOIL (goe229-il) Reynolds number: 100,000 Max Cl/Cd: 45.24 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe229-il-100000.txt Download as CSV file: xf-goe229-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 229 (MVA H.39) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.1330 0.11093 0.10677 -0.0850 0.9441 0.1837
-9.500 -0.0930 0.10667 0.10245 -0.0871 0.9413 0.1881
-9.250 -0.3382 0.06981 0.06550 -0.1135 0.9167 0.0876
-9.000 -0.3497 0.06283 0.05828 -0.1211 0.9067 0.0846
-8.750 -0.3707 0.05753 0.05256 -0.1241 0.8938 0.0814
-8.500 -0.3664 0.05230 0.04615 -0.1304 0.8846 0.0771
-8.250 -0.3464 0.04888 0.04245 -0.1316 0.8766 0.0763
-8.000 -0.3081 0.04480 0.03796 -0.1357 0.8731 0.0757
-7.750 -0.2933 0.04299 0.03583 -0.1351 0.8630 0.0760
-7.500 -0.2557 0.04025 0.03273 -0.1381 0.8584 0.0778
-7.250 -0.2105 0.03769 0.03008 -0.1414 0.8559 0.0798
-7.000 -0.1976 0.03686 0.02920 -0.1393 0.8449 0.0808
-6.750 -0.1542 0.03527 0.02752 -0.1419 0.8413 0.0845
-6.500 -0.1065 0.03376 0.02587 -0.1447 0.8390 0.0886
-6.250 -0.0950 0.03348 0.02558 -0.1421 0.8272 0.0901
-6.000 -0.0566 0.03210 0.02443 -0.1433 0.8240 0.0952
-5.750 -0.0379 0.03186 0.02420 -0.1421 0.8146 0.1006
-5.500 -0.0032 0.03092 0.02327 -0.1433 0.8092 0.1078
-5.250 0.0425 0.02933 0.02165 -0.1472 0.8064 0.1229
-5.000 0.0672 0.02740 0.02052 -0.1504 0.7960 0.2321
-4.750 0.1055 0.02858 0.02198 -0.1504 0.7915 0.3930
-4.500 0.1244 0.03019 0.02365 -0.1473 0.7832 0.4146
-4.250 0.1478 0.03160 0.02509 -0.1445 0.7764 0.4337
-4.000 0.1832 0.03216 0.02557 -0.1439 0.7734 0.4491
-3.750 0.1965 0.03287 0.02613 -0.1424 0.7626 0.4612
-3.500 0.2233 0.03382 0.02719 -0.1393 0.7586 0.4726
-3.250 0.2571 0.03416 0.02749 -0.1381 0.7559 0.4865
-3.000 0.2618 0.03516 0.02845 -0.1354 0.7443 0.4980
-2.750 0.2922 0.03556 0.02881 -0.1340 0.7412 0.5146
-2.500 0.2915 0.03696 0.03032 -0.1286 0.7318 0.5210
-2.250 0.3251 0.03652 0.02971 -0.1305 0.7270 0.5324
-2.000 0.3617 0.03586 0.02896 -0.1314 0.7243 0.5371
-1.750 0.3658 0.03686 0.02995 -0.1294 0.7146 0.5417
-1.500 0.4038 0.03628 0.02915 -0.1330 0.7104 0.5489
-1.250 0.4390 0.03572 0.02855 -0.1337 0.7079 0.5530
-1.000 0.4362 0.03729 0.03015 -0.1307 0.6980 0.5566
-0.750 0.4790 0.03637 0.02906 -0.1337 0.6938 0.5636
-0.500 0.5359 0.03428 0.02682 -0.1372 0.6912 0.5692
-0.250 0.5457 0.03501 0.02756 -0.1351 0.6822 0.5731
0.000 0.6109 0.03218 0.02447 -0.1398 0.6760 0.5806
0.250 0.6533 0.03041 0.02254 -0.1411 0.6654 0.5858
0.500 0.7090 0.02800 0.01985 -0.1438 0.6553 0.5920
0.750 0.7279 0.02796 0.01980 -0.1430 0.6442 0.5968
1.000 0.7650 0.02715 0.01882 -0.1446 0.6361 0.6021
1.250 0.7896 0.02677 0.01842 -0.1438 0.6262 0.6066
1.500 0.8172 0.02638 0.01796 -0.1438 0.6165 0.6121
1.750 0.8538 0.02572 0.01710 -0.1456 0.6072 0.6180
2.000 0.8725 0.02567 0.01711 -0.1442 0.5976 0.6219
2.250 0.9062 0.02516 0.01647 -0.1450 0.5897 0.6279
2.500 0.9263 0.02527 0.01659 -0.1443 0.5799 0.6339
2.750 0.9566 0.02489 0.01612 -0.1447 0.5718 0.6390
3.000 0.9755 0.02494 0.01622 -0.1434 0.5619 0.6440
3.250 1.0020 0.02481 0.01600 -0.1435 0.5523 0.6509
3.500 1.0243 0.02468 0.01584 -0.1426 0.5419 0.6566
3.750 1.0427 0.02475 0.01594 -0.1413 0.5311 0.6632
4.000 1.0672 0.02469 0.01578 -0.1411 0.5208 0.6701
4.250 1.0839 0.02483 0.01599 -0.1395 0.5109 0.6761
4.500 1.1066 0.02496 0.01609 -0.1391 0.5029 0.6842
4.750 1.1227 0.02513 0.01633 -0.1374 0.4937 0.6913
5.000 1.1396 0.02535 0.01655 -0.1361 0.4845 0.7004
5.250 1.1546 0.02555 0.01681 -0.1343 0.4759 0.7085
5.500 1.1709 0.02592 0.01724 -0.1330 0.4673 0.7182
5.750 1.1870 0.02624 0.01761 -0.1316 0.4586 0.7277
6.000 1.2012 0.02674 0.01819 -0.1301 0.4497 0.7388
6.250 1.2170 0.02717 0.01865 -0.1288 0.4408 0.7520
6.500 1.2286 0.02782 0.01945 -0.1271 0.4313 0.7665
6.750 1.2418 0.02835 0.02006 -0.1255 0.4223 0.7836
7.000 1.2518 0.02906 0.02094 -0.1236 0.4120 0.8048
7.250 1.2609 0.02968 0.02175 -0.1216 0.4020 0.8411
7.500 1.2647 0.03030 0.02252 -0.1189 0.3912 1.0000
7.750 1.2780 0.03154 0.02370 -0.1186 0.3775 1.0000
8.000 1.2888 0.03287 0.02495 -0.1177 0.3633 1.0000
8.250 1.2974 0.03431 0.02631 -0.1166 0.3491 1.0000
8.500 1.3044 0.03587 0.02780 -0.1153 0.3357 1.0000
8.750 1.3103 0.03755 0.02944 -0.1140 0.3239 1.0000
9.000 1.3149 0.03937 0.03121 -0.1126 0.3134 1.0000
9.250 1.3202 0.04121 0.03304 -0.1114 0.3041 1.0000
9.500 1.3241 0.04318 0.03499 -0.1101 0.2963 1.0000
9.750 1.3293 0.04513 0.03696 -0.1090 0.2890 1.0000
10.000 1.3332 0.04720 0.03903 -0.1079 0.2828 1.0000
10.250 1.3388 0.04918 0.04106 -0.1069 0.2774 1.0000
10.500 1.3434 0.05129 0.04321 -0.1060 0.2716 1.0000
10.750 1.3460 0.05359 0.04548 -0.1049 0.2655 1.0000
11.000 1.3493 0.05595 0.04788 -0.1041 0.2584 1.0000
11.250 1.3496 0.05857 0.05048 -0.1032 0.2510 1.0000
11.500 1.3512 0.06119 0.05313 -0.1025 0.2435 1.0000
11.750 1.3516 0.06394 0.05588 -0.1018 0.2361 1.0000
12.000 1.3545 0.06648 0.05847 -0.1013 0.2300 1.0000
12.250 1.3576 0.06905 0.06110 -0.1008 0.2242 1.0000
12.500 1.3612 0.07151 0.06358 -0.1003 0.2197 1.0000
12.750 1.3654 0.07402 0.06617 -0.0999 0.2147 1.0000
13.000 1.3672 0.07686 0.06909 -0.0997 0.2085 1.0000
13.250 1.3672 0.07988 0.07213 -0.0994 0.2021 1.0000
13.500 1.3697 0.08277 0.07515 -0.0993 0.1955 1.0000
13.750 1.3719 0.08562 0.07807 -0.0992 0.1904 1.0000
14.000 1.3748 0.08841 0.08097 -0.0991 0.1855 1.0000
14.250 1.3772 0.09135 0.08404 -0.0992 0.1787 1.0000
14.500 1.3779 0.09454 0.08733 -0.0993 0.1708 1.0000
14.750 1.3777 0.09787 0.09075 -0.0995 0.1579 1.0000
15.000 1.3697 0.10226 0.09509 -0.1000 0.1414 1.0000
15.250 1.3591 0.10707 0.09979 -0.1006 0.1321 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 229 (MVA H.39) AIRFOIL (goe229-il)