GOE 413 AIRFOIL (goe413-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 413 AIRFOIL (goe413-il) Reynolds number: 100,000 Max Cl/Cd: 47.3 at α=9.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe413-il-100000.txt Download as CSV file: xf-goe413-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 413 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2213 0.12256 0.11751 -0.0387 1.0000 0.1518
-10.000 -0.2507 0.12379 0.11887 -0.0354 1.0000 0.1545
-9.750 -0.3034 0.12533 0.12056 -0.0386 0.9964 0.1564
-9.500 -0.2532 0.11860 0.11377 -0.0391 0.9936 0.1579
-9.250 -0.2177 0.11408 0.10923 -0.0423 0.9884 0.1605
-9.000 -0.1916 0.11008 0.10520 -0.0472 0.9825 0.1647
-8.750 -0.2138 0.10710 0.10226 -0.0607 0.9710 0.1714
-8.500 -0.1615 0.10137 0.09647 -0.0608 0.9689 0.1734
-8.250 -0.1236 0.09730 0.09238 -0.0643 0.9646 0.1772
-8.000 -0.1061 0.09394 0.08900 -0.0690 0.9537 0.1830
-7.750 -0.1205 0.09013 0.08522 -0.0783 0.9378 0.1880
-7.500 -0.2219 0.05690 0.05150 -0.1124 0.9144 0.1191
-7.250 -0.2128 0.05299 0.04748 -0.1144 0.9011 0.1169
-7.000 -0.2155 0.04538 0.03938 -0.1203 0.8892 0.1137
-6.750 -0.2074 0.03985 0.03323 -0.1236 0.8779 0.1126
-6.500 -0.1908 0.03681 0.02974 -0.1246 0.8674 0.1128
-6.250 -0.1677 0.03429 0.02679 -0.1255 0.8586 0.1132
-6.000 -0.1443 0.03246 0.02461 -0.1257 0.8497 0.1137
-5.750 -0.1200 0.03100 0.02286 -0.1257 0.8405 0.1147
-5.500 -0.0906 0.02959 0.02115 -0.1259 0.8351 0.1163
-5.250 -0.0689 0.02887 0.02016 -0.1255 0.8242 0.1183
-5.000 -0.0410 0.02799 0.01932 -0.1253 0.8176 0.1210
-4.750 -0.0158 0.02751 0.01881 -0.1249 0.8096 0.1240
-4.500 0.0100 0.02693 0.01812 -0.1245 0.8014 0.1272
-4.250 0.0391 0.02615 0.01723 -0.1242 0.7962 0.1309
-4.000 0.0627 0.02593 0.01712 -0.1238 0.7876 0.1353
-3.750 0.0900 0.02551 0.01659 -0.1235 0.7804 0.1425
-3.500 0.1190 0.02498 0.01615 -0.1233 0.7757 0.1528
-3.250 0.1427 0.02491 0.01619 -0.1230 0.7672 0.1672
-3.000 0.1701 0.02446 0.01590 -0.1229 0.7605 0.1997
-2.750 0.2000 0.02415 0.01568 -0.1228 0.7559 0.2443
-2.500 0.2238 0.02460 0.01618 -0.1226 0.7478 0.2707
-2.250 0.2508 0.02476 0.01634 -0.1223 0.7411 0.2925
-2.000 0.2805 0.02468 0.01623 -0.1220 0.7365 0.3129
-1.750 0.3049 0.02499 0.01656 -0.1217 0.7291 0.3276
-1.500 0.3315 0.02510 0.01663 -0.1215 0.7222 0.3436
-1.250 0.3618 0.02486 0.01633 -0.1212 0.7175 0.3614
-1.000 0.3869 0.02501 0.01658 -0.1208 0.7109 0.3783
-0.750 0.4123 0.02511 0.01675 -0.1205 0.7034 0.3961
-0.500 0.4423 0.02475 0.01642 -0.1202 0.6987 0.4190
-0.250 0.4699 0.02472 0.01643 -0.1198 0.6933 0.4466
0.000 0.4924 0.02503 0.01695 -0.1192 0.6849 0.4744
0.250 0.5217 0.02476 0.01674 -0.1187 0.6800 0.5114
0.500 0.5526 0.02433 0.01637 -0.1180 0.6765 0.5502
0.750 0.5702 0.02507 0.01734 -0.1172 0.6663 0.5845
1.000 0.5980 0.02471 0.01710 -0.1163 0.6612 0.6300
1.250 0.6265 0.02415 0.01667 -0.1150 0.6575 0.6821
1.500 0.6398 0.02492 0.01775 -0.1130 0.6477 0.7374
1.750 0.6580 0.02457 0.01760 -0.1098 0.6423 0.8193
2.000 0.6890 0.02379 0.01688 -0.1085 0.6383 1.0000
2.250 0.7115 0.02489 0.01790 -0.1092 0.6282 1.0000
2.500 0.7446 0.02488 0.01770 -0.1098 0.6224 1.0000
2.750 0.7807 0.02464 0.01725 -0.1104 0.6183 1.0000
3.000 0.7977 0.02586 0.01850 -0.1099 0.6076 1.0000
3.250 0.8298 0.02580 0.01830 -0.1100 0.6019 1.0000
3.500 0.8659 0.02555 0.01787 -0.1104 0.5978 1.0000
3.750 0.8798 0.02691 0.01932 -0.1095 0.5865 1.0000
4.000 0.9129 0.02674 0.01903 -0.1096 0.5810 1.0000
4.250 0.9368 0.02738 0.01965 -0.1092 0.5735 1.0000
4.500 0.9601 0.02797 0.02023 -0.1087 0.5650 1.0000
4.750 0.9951 0.02768 0.01981 -0.1089 0.5601 1.0000
5.000 1.0109 0.02886 0.02107 -0.1079 0.5504 1.0000
5.250 1.0398 0.02897 0.02113 -0.1077 0.5437 1.0000
5.500 1.0770 0.02859 0.02060 -0.1081 0.5393 1.0000
5.750 1.0868 0.03007 0.02224 -0.1066 0.5283 1.0000
6.000 1.1219 0.02959 0.02165 -0.1067 0.5224 1.0000
6.250 1.1419 0.03026 0.02236 -0.1057 0.5136 1.0000
6.500 1.1702 0.03009 0.02215 -0.1053 0.5054 1.0000
6.750 1.2052 0.02950 0.02143 -0.1053 0.4986 1.0000
7.000 1.2217 0.03012 0.02215 -0.1039 0.4882 1.0000
7.250 1.2618 0.02924 0.02107 -0.1045 0.4825 1.0000
7.500 1.2712 0.03038 0.02240 -0.1026 0.4721 1.0000
7.750 1.3068 0.02974 0.02163 -0.1028 0.4654 1.0000
8.000 1.3216 0.03055 0.02255 -0.1013 0.4564 1.0000
8.250 1.3496 0.03043 0.02239 -0.1008 0.4490 1.0000
8.500 1.3738 0.03063 0.02259 -0.1001 0.4414 1.0000
8.750 1.3925 0.03097 0.02299 -0.0988 0.4325 1.0000
9.000 1.4239 0.03068 0.02260 -0.0988 0.4253 1.0000
9.250 1.4333 0.03165 0.02375 -0.0967 0.4166 1.0000
9.500 1.4700 0.03108 0.02301 -0.0971 0.4098 1.0000
9.750 1.4724 0.03230 0.02445 -0.0943 0.4007 1.0000
10.000 1.5039 0.03194 0.02398 -0.0942 0.3930 1.0000
10.250 1.5078 0.03303 0.02524 -0.0915 0.3845 1.0000
10.500 1.5341 0.03279 0.02490 -0.0908 0.3756 1.0000
10.750 1.5326 0.03391 0.02617 -0.0874 0.3668 1.0000
11.000 1.5562 0.03369 0.02583 -0.0863 0.3570 1.0000
11.250 1.5470 0.03537 0.02772 -0.0827 0.3485 1.0000
11.500 1.5684 0.03538 0.02760 -0.0816 0.3391 1.0000
11.750 1.5553 0.03757 0.03002 -0.0783 0.3302 1.0000
12.000 1.5658 0.03827 0.03068 -0.0767 0.3203 1.0000
12.250 1.5558 0.04058 0.03315 -0.0743 0.3101 1.0000
12.500 1.5519 0.04258 0.03522 -0.0724 0.2990 1.0000
12.750 1.5487 0.04455 0.03718 -0.0707 0.2864 1.0000
13.000 1.5353 0.04769 0.04041 -0.0692 0.2727 1.0000
13.250 1.5184 0.05147 0.04426 -0.0680 0.2572 1.0000
13.500 1.5013 0.05548 0.04824 -0.0672 0.2394 1.0000
13.750 1.4793 0.06049 0.05325 -0.0668 0.2197 1.0000
14.000 1.4600 0.06546 0.05812 -0.0666 0.2001 1.0000
14.250 1.4457 0.06994 0.06245 -0.0664 0.1841 1.0000
14.500 1.4372 0.07383 0.06622 -0.0661 0.1720 1.0000
14.750 1.4349 0.07689 0.06911 -0.0656 0.1633 1.0000
15.000 1.4348 0.07982 0.07203 -0.0653 0.1562 1.0000
15.250 1.4420 0.08162 0.07370 -0.0645 0.1508 1.0000
15.500 1.4477 0.08389 0.07601 -0.0640 0.1462 1.0000
15.750 1.4584 0.08533 0.07739 -0.0631 0.1425 1.0000
16.000 1.4772 0.08558 0.07750 -0.0617 0.1392 1.0000
16.250 1.4839 0.08781 0.07987 -0.0613 0.1368 1.0000
16.500 1.4935 0.08962 0.08175 -0.0607 0.1344 1.0000
16.750 1.5060 0.09102 0.08318 -0.0600 0.1322 1.0000
17.000 1.5242 0.09159 0.08370 -0.0589 0.1301 1.0000
17.250 1.5532 0.09082 0.08278 -0.0571 0.1279 1.0000
17.500 1.5520 0.09424 0.08642 -0.0574 0.1267 1.0000
17.750 1.5510 0.09767 0.09005 -0.0577 0.1255 1.0000
18.000 1.5492 0.10126 0.09384 -0.0582 0.1245 1.0000
18.250 1.5450 0.10526 0.09804 -0.0589 0.1236 1.0000
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