GOE 342 AIRFOIL (goe342-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 342 AIRFOIL (goe342-il) Reynolds number: 100,000 Max Cl/Cd: 71.31 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe342-il-100000.txt Download as CSV file: xf-goe342-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 342 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.3122 0.10124 0.09669 -0.0209 1.0000 0.0425
-7.000 -0.3234 0.10050 0.09603 -0.0182 1.0000 0.0431
-6.750 -0.3329 0.09967 0.09529 -0.0162 1.0000 0.0438
-6.500 -0.3403 0.09882 0.09451 -0.0152 1.0000 0.0445
-6.250 -0.3438 0.09815 0.09389 -0.0160 1.0000 0.0453
-6.000 -0.3392 0.09789 0.09365 -0.0206 1.0000 0.0458
-5.750 -0.3222 0.09728 0.09300 -0.0289 1.0000 0.0462
-5.500 -0.3244 0.09256 0.08835 -0.0254 1.0000 0.0466
-5.250 -0.3276 0.08857 0.08441 -0.0208 1.0000 0.0474
-5.000 -0.3240 0.08558 0.08145 -0.0194 1.0000 0.0484
-4.750 -0.3156 0.08287 0.07874 -0.0201 1.0000 0.0498
-4.500 -0.3025 0.08016 0.07602 -0.0223 1.0000 0.0517
-4.250 -0.2204 0.07784 0.07340 -0.0460 0.9965 0.0574
-4.000 -0.2200 0.07250 0.06816 -0.0418 0.9943 0.0587
-3.750 -0.2000 0.06899 0.06463 -0.0434 0.9911 0.0613
-3.500 -0.1089 0.06726 0.06244 -0.0648 0.9867 0.0698
-3.250 -0.1033 0.06173 0.05708 -0.0626 0.9845 0.0714
-3.000 -0.0797 0.05871 0.05405 -0.0644 0.9813 0.0762
-2.750 -0.0273 0.05560 0.05072 -0.0740 0.9774 0.0849
-2.500 0.0045 0.05281 0.04790 -0.0774 0.9740 0.0914
-2.250 0.0592 0.04964 0.04453 -0.0861 0.9707 0.1003
-2.000 0.1072 0.04731 0.04195 -0.0928 0.9648 0.1119
-1.750 0.1552 0.04451 0.03903 -0.0990 0.9588 0.1269
-1.500 0.2008 0.04204 0.03647 -0.1042 0.9520 0.1444
-1.250 0.2539 0.03981 0.03403 -0.1108 0.9445 0.1715
-1.000 0.3000 0.03760 0.03175 -0.1156 0.9375 0.2025
-0.250 0.4200 0.03104 0.02535 -0.1246 0.9159 0.4107
0.000 0.4694 0.02893 0.02326 -0.1286 0.9122 0.4710
0.250 0.5089 0.02796 0.02213 -0.1313 0.9043 0.4821
0.500 0.6036 0.02762 0.01997 -0.1408 0.8992 0.1467
0.750 0.6501 0.02638 0.01832 -0.1430 0.8936 0.1181
1.000 0.6901 0.02544 0.01716 -0.1446 0.8860 0.1133
1.250 0.7416 0.02416 0.01573 -0.1478 0.8819 0.1075
1.500 0.7697 0.02363 0.01519 -0.1473 0.8714 0.1053
1.750 0.8121 0.02258 0.01415 -0.1489 0.8655 0.1048
2.000 0.8429 0.02199 0.01358 -0.1485 0.8550 0.1063
2.250 0.8745 0.02140 0.01299 -0.1481 0.8444 0.1114
2.500 0.9139 0.02040 0.01203 -0.1488 0.8365 0.1274
2.750 0.9434 0.01981 0.01163 -0.1480 0.8236 0.1665
3.000 0.9672 0.01825 0.01129 -0.1459 0.8104 1.0000
3.250 0.9957 0.01789 0.01081 -0.1446 0.7957 1.0000
3.500 1.0243 0.01745 0.01029 -0.1432 0.7793 1.0000
3.750 1.0506 0.01707 0.00985 -0.1414 0.7583 1.0000
4.000 1.0771 0.01666 0.00941 -0.1396 0.7336 1.0000
4.250 1.1019 0.01639 0.00905 -0.1377 0.7027 1.0000
4.500 1.1246 0.01627 0.00887 -0.1357 0.6624 1.0000
4.750 1.1479 0.01626 0.00872 -0.1339 0.6186 1.0000
5.000 1.1716 0.01643 0.00869 -0.1324 0.5795 1.0000
5.250 1.1954 0.01685 0.00888 -0.1312 0.5477 1.0000
5.500 1.2189 0.01743 0.00923 -0.1301 0.5212 1.0000
5.750 1.2418 0.01807 0.00971 -0.1290 0.4960 1.0000
6.000 1.2641 0.01873 0.01029 -0.1279 0.4714 1.0000
6.250 1.2867 0.01940 0.01086 -0.1268 0.4503 1.0000
6.500 1.3094 0.02005 0.01150 -0.1259 0.4315 1.0000
6.750 1.3311 0.02067 0.01218 -0.1248 0.4116 1.0000
7.000 1.3521 0.02133 0.01287 -0.1235 0.3909 1.0000
7.250 1.3718 0.02198 0.01359 -0.1220 0.3683 1.0000
7.500 1.3890 0.02266 0.01430 -0.1201 0.3401 1.0000
7.750 1.4020 0.02339 0.01506 -0.1176 0.3006 1.0000
8.000 1.4111 0.02431 0.01588 -0.1145 0.2424 1.0000
8.250 1.4197 0.02569 0.01692 -0.1115 0.1924 1.0000
8.500 1.4285 0.02735 0.01828 -0.1089 0.1611 1.0000
8.750 1.4359 0.02927 0.01993 -0.1061 0.1407 1.0000
9.000 1.4455 0.03119 0.02181 -0.1036 0.1241 1.0000
9.250 1.4551 0.03327 0.02387 -0.1011 0.1081 1.0000
9.500 1.4645 0.03548 0.02607 -0.0986 0.0922 1.0000
9.750 1.4759 0.03777 0.02841 -0.0963 0.0791 1.0000
10.000 1.4885 0.03998 0.03064 -0.0943 0.0698 1.0000
10.250 1.5036 0.04209 0.03272 -0.0927 0.0631 1.0000
10.500 1.5265 0.04534 0.03623 -0.0919 0.0583 1.0000
10.750 1.5391 0.04767 0.03881 -0.0899 0.0545 1.0000
11.000 1.5584 0.05124 0.04233 -0.0896 0.0505 1.0000
11.250 1.5632 0.05443 0.04600 -0.0868 0.0492 1.0000
11.500 1.5631 0.05768 0.04969 -0.0835 0.0484 1.0000
11.750 1.5572 0.06105 0.05347 -0.0797 0.0478 1.0000
12.000 1.5471 0.06460 0.05739 -0.0760 0.0475 1.0000
12.250 1.5332 0.06838 0.06153 -0.0726 0.0474 1.0000
12.500 1.5166 0.07241 0.06589 -0.0697 0.0473 1.0000
12.750 1.4975 0.07678 0.07057 -0.0675 0.0473 1.0000
13.000 1.4766 0.08155 0.07563 -0.0660 0.0474 1.0000
13.250 1.4540 0.08679 0.08114 -0.0655 0.0476 1.0000
13.500 1.4301 0.09257 0.08717 -0.0659 0.0478 1.0000
13.750 1.4054 0.09890 0.09372 -0.0673 0.0481 1.0000
14.000 1.3807 0.10583 0.10085 -0.0697 0.0486 1.0000
14.250 1.3559 0.11343 0.10862 -0.0733 0.0490 1.0000
14.500 1.3327 0.12162 0.11696 -0.0777 0.0495 1.0000
14.750 1.3121 0.13027 0.12568 -0.0825 0.0500 1.0000
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