GOE 505 AIRFOIL (goe505-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 505 AIRFOIL (goe505-il) Reynolds number: 100,000 Max Cl/Cd: 49.13 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe505-il-100000.txt Download as CSV file: xf-goe505-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 505 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 -0.3801 0.11393 0.10998 -0.0189 0.9931 0.1195
-7.000 -0.4122 0.11296 0.10907 -0.0221 0.9865 0.1218
-6.750 -0.4295 0.10950 0.10560 -0.0290 0.9792 0.1232
-6.500 -0.3874 0.10483 0.10095 -0.0257 0.9743 0.1261
-6.250 -0.3695 0.10175 0.09783 -0.0280 0.9681 0.1296
-6.000 -0.3708 0.09892 0.09499 -0.0300 0.9602 0.1338
-5.750 -0.3825 0.09510 0.09104 -0.0385 0.9510 0.1385
-5.500 -0.3625 0.09145 0.08744 -0.0368 0.9446 0.1402
-5.250 -0.3420 0.08858 0.08455 -0.0375 0.9376 0.1440
-5.000 -0.3366 0.08516 0.08084 -0.0453 0.9277 0.1537
-4.750 -0.3211 0.08179 0.07758 -0.0431 0.9202 0.1557
-4.500 -0.2983 0.07907 0.07483 -0.0436 0.9125 0.1608
-4.250 -0.2840 0.07561 0.07109 -0.0483 0.9012 0.1702
-4.000 -0.2660 0.05881 0.05302 -0.0556 0.8973 0.1082
-3.750 -0.2415 0.05727 0.05171 -0.0556 0.8854 0.1107
-3.500 -0.2021 0.05014 0.04389 -0.0591 0.8795 0.1003
-3.250 -0.1927 0.04465 0.03749 -0.0565 0.8685 0.0971
-3.000 -0.1624 0.04155 0.03371 -0.0565 0.8591 0.0966
-2.750 -0.1238 0.03962 0.03143 -0.0579 0.8508 0.0985
-2.500 -0.0999 0.03846 0.03002 -0.0570 0.8408 0.1005
-2.250 -0.0587 0.03715 0.02835 -0.0587 0.8347 0.1060
-2.000 -0.0356 0.03630 0.02738 -0.0576 0.8245 0.1113
-1.750 0.0084 0.03524 0.02613 -0.0596 0.8186 0.1219
-1.500 0.0305 0.03469 0.02567 -0.0584 0.8080 0.1335
-1.250 0.0737 0.03398 0.02494 -0.0602 0.8022 0.1692
-1.000 0.0933 0.03397 0.02507 -0.0585 0.7906 0.1943
-0.750 0.1375 0.03337 0.02446 -0.0606 0.7855 0.2241
-0.500 0.1563 0.03334 0.02446 -0.0588 0.7733 0.2450
-0.250 0.2027 0.03251 0.02365 -0.0610 0.7689 0.2756
0.000 0.2234 0.03218 0.02332 -0.0594 0.7564 0.2931
0.250 0.2732 0.03095 0.02203 -0.0620 0.7527 0.3196
0.500 0.2946 0.03053 0.02162 -0.0605 0.7401 0.3366
0.750 0.3466 0.02900 0.02016 -0.0635 0.7369 0.3629
1.250 0.6416 0.02322 0.01619 -0.1069 0.7374 1.0000
1.500 0.4648 0.02544 0.01698 -0.0671 0.7094 0.4661
1.750 0.6967 0.02193 0.01454 -0.1047 0.7098 1.0000
2.000 0.7329 0.02108 0.01354 -0.1052 0.6947 1.0000
2.250 0.7739 0.02021 0.01249 -0.1066 0.6770 1.0000
2.500 0.8187 0.01945 0.01151 -0.1089 0.6554 1.0000
2.750 0.8541 0.01906 0.01088 -0.1096 0.6292 1.0000
3.000 0.8873 0.01898 0.01050 -0.1102 0.6029 1.0000
3.250 0.9204 0.01909 0.01030 -0.1109 0.5793 1.0000
3.500 0.9449 0.01943 0.01039 -0.1102 0.5586 1.0000
3.750 0.9677 0.01982 0.01057 -0.1092 0.5413 1.0000
4.000 0.9930 0.02024 0.01079 -0.1088 0.5268 1.0000
4.250 1.0166 0.02069 0.01109 -0.1081 0.5142 1.0000
4.500 1.0349 0.02118 0.01150 -0.1064 0.5028 1.0000
4.750 1.0593 0.02167 0.01186 -0.1059 0.4927 1.0000
5.000 1.0810 0.02213 0.01222 -0.1049 0.4828 1.0000
5.250 1.0981 0.02264 0.01270 -0.1030 0.4734 1.0000
5.500 1.1257 0.02312 0.01301 -0.1032 0.4645 1.0000
5.750 1.1365 0.02364 0.01358 -0.1002 0.4560 1.0000
6.000 1.1656 0.02415 0.01395 -0.1006 0.4483 1.0000
6.250 1.1774 0.02473 0.01461 -0.0979 0.4413 1.0000
6.500 1.2002 0.02527 0.01510 -0.0971 0.4345 1.0000
6.750 1.2222 0.02590 0.01571 -0.0964 0.4283 1.0000
7.000 1.2354 0.02650 0.01640 -0.0939 0.4220 1.0000
7.250 1.2660 0.02710 0.01690 -0.0947 0.4161 1.0000
7.500 1.2782 0.02783 0.01773 -0.0922 0.4106 1.0000
7.750 1.2924 0.02849 0.01848 -0.0900 0.4047 1.0000
8.000 1.3278 0.02915 0.01901 -0.0918 0.3988 1.0000
8.250 1.3303 0.02993 0.01999 -0.0875 0.3934 1.0000
8.500 1.3446 0.03061 0.02074 -0.0854 0.3875 1.0000
8.750 1.3803 0.03133 0.02136 -0.0872 0.3817 1.0000
9.000 1.3764 0.03218 0.02245 -0.0819 0.3763 1.0000
9.250 1.3930 0.03270 0.02297 -0.0802 0.3693 1.0000
9.500 1.4060 0.03333 0.02362 -0.0779 0.3621 1.0000
9.750 1.4096 0.03389 0.02428 -0.0740 0.3550 1.0000
10.000 1.4281 0.03422 0.02453 -0.0726 0.3468 1.0000
10.250 1.4218 0.03494 0.02541 -0.0670 0.3411 1.0000
10.500 1.4542 0.03504 0.02531 -0.0680 0.3326 1.0000
10.750 1.4393 0.03601 0.02654 -0.0612 0.3281 1.0000
11.000 1.4431 0.03664 0.02728 -0.0577 0.3222 1.0000
11.250 1.4673 0.03690 0.02745 -0.0574 0.3154 1.0000
11.500 1.4510 0.03792 0.02870 -0.0511 0.3098 1.0000
11.750 1.4674 0.03794 0.02864 -0.0495 0.3026 1.0000
12.000 1.4671 0.03892 0.02976 -0.0459 0.2976 1.0000
12.250 1.4596 0.04010 0.03114 -0.0416 0.2926 1.0000
12.500 1.4785 0.04006 0.03104 -0.0405 0.2861 1.0000
12.750 1.4648 0.04144 0.03262 -0.0358 0.2805 1.0000
13.000 1.4591 0.04260 0.03392 -0.0323 0.2749 1.0000
13.250 1.4685 0.04278 0.03404 -0.0303 0.2681 1.0000
13.500 1.4532 0.04486 0.03639 -0.0264 0.2633 1.0000
13.750 1.4519 0.04588 0.03749 -0.0238 0.2570 1.0000
14.000 1.4469 0.04736 0.03907 -0.0213 0.2512 1.0000
14.250 1.4352 0.04965 0.04158 -0.0186 0.2456 1.0000
14.500 1.4387 0.05070 0.04266 -0.0170 0.2399 1.0000
14.750 1.4243 0.05366 0.04585 -0.0149 0.2346 1.0000
15.000 1.4140 0.05634 0.04868 -0.0132 0.2282 1.0000
15.250 1.4055 0.05906 0.05149 -0.0120 0.2219 1.0000
15.500 1.3902 0.06297 0.05562 -0.0111 0.2165 1.0000
15.750 1.3845 0.06581 0.05849 -0.0105 0.2096 1.0000
16.000 1.3623 0.07118 0.06411 -0.0104 0.2049 1.0000
16.250 1.3463 0.07589 0.06894 -0.0107 0.1985 1.0000
16.500 1.3243 0.08178 0.07497 -0.0115 0.1931 1.0000
16.750 1.2930 0.08939 0.08278 -0.0130 0.1903 1.0000
17.000 1.2599 0.09765 0.09124 -0.0150 0.1898 1.0000
17.250 1.2590 0.10081 0.09440 -0.0158 0.1809 1.0000
17.500 1.2226 0.11002 0.10380 -0.0186 0.1801 1.0000
17.750 1.1728 0.12201 0.11592 -0.0225 0.1803 1.0000
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Polar data table (+)
Polar graphs
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