GOE 418 AIRFOIL (goe418-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 418 AIRFOIL (goe418-il) Reynolds number: 500,000 Max Cl/Cd: 101.57 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe418-il-500000.txt Download as CSV file: xf-goe418-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 418 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.750 -0.3080 0.13318 0.13049 -0.0306 1.0000 0.0461
-12.500 -0.3012 0.13059 0.12792 -0.0312 1.0000 0.0469
-10.500 -0.6421 0.02771 0.02386 -0.1019 0.9764 0.0530
-10.250 -0.6186 0.02455 0.02024 -0.1044 0.9710 0.0541
-10.000 -0.5886 0.02237 0.01773 -0.1067 0.9681 0.0551
-9.750 -0.5586 0.02174 0.01715 -0.1074 0.9623 0.0559
-9.500 -0.5251 0.02122 0.01661 -0.1086 0.9576 0.0567
-9.250 -0.4906 0.02044 0.01574 -0.1103 0.9537 0.0576
-9.000 -0.4627 0.01950 0.01464 -0.1107 0.9458 0.0586
-8.750 -0.4314 0.01845 0.01337 -0.1118 0.9389 0.0597
-8.500 -0.4044 0.01743 0.01214 -0.1119 0.9295 0.0607
-8.250 -0.3739 0.01688 0.01158 -0.1124 0.9207 0.0617
-8.000 -0.3467 0.01666 0.01135 -0.1120 0.9098 0.0627
-7.750 -0.3183 0.01630 0.01090 -0.1119 0.9000 0.0638
-7.500 -0.2937 0.01580 0.01027 -0.1111 0.8879 0.0649
-7.250 -0.2683 0.01531 0.00960 -0.1104 0.8764 0.0661
-7.000 -0.2434 0.01466 0.00881 -0.1097 0.8639 0.0672
-6.750 -0.2181 0.01441 0.00855 -0.1089 0.8499 0.0683
-6.500 -0.1918 0.01429 0.00839 -0.1082 0.8358 0.0694
-6.250 -0.1658 0.01410 0.00811 -0.1075 0.8209 0.0708
-6.000 -0.1403 0.01380 0.00764 -0.1067 0.8043 0.0723
-5.750 -0.1152 0.01341 0.00708 -0.1058 0.7859 0.0736
-5.500 -0.0899 0.01318 0.00680 -0.1050 0.7664 0.0749
-5.250 -0.0640 0.01315 0.00670 -0.1043 0.7468 0.0763
-5.000 -0.0380 0.01308 0.00653 -0.1035 0.7286 0.0779
-4.750 -0.0118 0.01294 0.00625 -0.1028 0.7126 0.0798
-4.500 0.0140 0.01265 0.00583 -0.1021 0.6987 0.0814
-4.250 0.0402 0.01257 0.00570 -0.1015 0.6864 0.0829
-4.000 0.0670 0.01255 0.00565 -0.1010 0.6747 0.0847
-3.750 0.0938 0.01253 0.00553 -0.1004 0.6636 0.0869
-3.500 0.1205 0.01254 0.00539 -0.0998 0.6525 0.0888
-3.250 0.1468 0.01219 0.00505 -0.0993 0.6436 0.0910
-3.000 0.1739 0.01215 0.00500 -0.0988 0.6357 0.0930
-2.750 0.2011 0.01216 0.00493 -0.0984 0.6289 0.0955
-2.500 0.2288 0.01215 0.00487 -0.0980 0.6223 0.0977
-2.250 0.2554 0.01181 0.00453 -0.0975 0.6158 0.1004
-2.000 0.2824 0.01179 0.00447 -0.0971 0.6097 0.1026
-1.750 0.3099 0.01170 0.00440 -0.0967 0.6032 0.1052
-1.500 0.3372 0.01170 0.00434 -0.0962 0.5962 0.1077
-1.250 0.3637 0.01150 0.00408 -0.0957 0.5897 0.1104
-1.000 0.3909 0.01131 0.00396 -0.0953 0.5841 0.1129
-0.750 0.4181 0.01125 0.00389 -0.0949 0.5779 0.1156
-0.500 0.4450 0.01126 0.00384 -0.0944 0.5714 0.1183
-0.250 0.4724 0.01120 0.00379 -0.0940 0.5652 0.1203
0.000 0.4988 0.01095 0.00355 -0.0934 0.5583 0.1232
0.250 0.5252 0.01090 0.00347 -0.0929 0.5520 0.1261
0.500 0.5524 0.01081 0.00344 -0.0925 0.5462 0.1288
0.750 0.5794 0.01077 0.00339 -0.0920 0.5400 0.1317
1.000 0.6061 0.01078 0.00336 -0.0915 0.5338 0.1338
1.250 0.6326 0.01064 0.00326 -0.0910 0.5269 0.1372
1.500 0.6588 0.01056 0.00320 -0.0904 0.5189 0.1406
1.750 0.6850 0.01057 0.00319 -0.0898 0.5118 0.1440
2.000 0.7119 0.01054 0.00319 -0.0893 0.5042 0.1478
2.250 0.7378 0.01054 0.00317 -0.0887 0.4965 0.1519
2.500 0.7642 0.01049 0.00319 -0.0882 0.4887 0.1585
2.750 0.7901 0.01051 0.00320 -0.0875 0.4798 0.1662
3.000 0.8158 0.01047 0.00326 -0.0869 0.4704 0.1878
3.250 0.8397 0.01035 0.00337 -0.0860 0.4591 0.2849
3.500 0.8955 0.00901 0.00365 -0.0922 0.4442 1.0000
3.750 0.9196 0.00915 0.00372 -0.0912 0.4325 1.0000
4.000 0.9430 0.00934 0.00382 -0.0901 0.4199 1.0000
4.250 0.9662 0.00954 0.00394 -0.0890 0.4056 1.0000
4.500 0.9894 0.00975 0.00407 -0.0880 0.3908 1.0000
4.750 1.0126 0.00997 0.00422 -0.0869 0.3780 1.0000
5.000 1.0352 0.01023 0.00439 -0.0857 0.3644 1.0000
5.250 1.0573 0.01052 0.00459 -0.0845 0.3516 1.0000
5.500 1.0804 0.01075 0.00478 -0.0835 0.3401 1.0000
5.750 1.1029 0.01102 0.00499 -0.0824 0.3290 1.0000
6.000 1.1243 0.01134 0.00523 -0.0811 0.3171 1.0000
6.250 1.1467 0.01160 0.00546 -0.0800 0.3045 1.0000
6.500 1.1681 0.01191 0.00572 -0.0787 0.2905 1.0000
6.750 1.1881 0.01228 0.00600 -0.0772 0.2726 1.0000
7.000 1.2058 0.01277 0.00635 -0.0754 0.2477 1.0000
7.250 1.2189 0.01348 0.00682 -0.0729 0.2079 1.0000
7.500 1.2280 0.01436 0.00744 -0.0698 0.1731 1.0000
7.750 1.2400 0.01498 0.00795 -0.0671 0.1591 1.0000
8.000 1.2535 0.01546 0.00840 -0.0646 0.1528 1.0000
8.250 1.2655 0.01601 0.00891 -0.0619 0.1476 1.0000
8.500 1.2801 0.01647 0.00938 -0.0596 0.1447 1.0000
8.750 1.2952 0.01692 0.00985 -0.0576 0.1423 1.0000
9.000 1.3093 0.01743 0.01037 -0.0555 0.1401 1.0000
9.250 1.3222 0.01802 0.01097 -0.0533 0.1379 1.0000
9.500 1.3336 0.01870 0.01165 -0.0510 0.1358 1.0000
9.750 1.3432 0.01951 0.01246 -0.0486 0.1336 1.0000
10.000 1.3572 0.02013 0.01314 -0.0468 0.1323 1.0000
10.250 1.3719 0.02074 0.01379 -0.0452 0.1308 1.0000
10.500 1.3853 0.02144 0.01454 -0.0436 0.1293 1.0000
10.750 1.3977 0.02223 0.01538 -0.0420 0.1280 1.0000
11.000 1.4091 0.02312 0.01631 -0.0403 0.1265 1.0000
11.250 1.4193 0.02413 0.01734 -0.0387 0.1250 1.0000
11.500 1.4277 0.02531 0.01854 -0.0370 0.1233 1.0000
11.750 1.4332 0.02673 0.01997 -0.0353 0.1212 1.0000
12.000 1.4451 0.02776 0.02107 -0.0341 0.1198 1.0000
12.250 1.4581 0.02874 0.02212 -0.0332 0.1185 1.0000
12.500 1.4697 0.02985 0.02330 -0.0322 0.1169 1.0000
12.750 1.4801 0.03109 0.02459 -0.0312 0.1155 1.0000
13.000 1.4897 0.03244 0.02600 -0.0303 0.1139 1.0000
13.250 1.4971 0.03401 0.02759 -0.0294 0.1123 1.0000
13.500 1.5022 0.03579 0.02940 -0.0284 0.1106 1.0000
13.750 1.5068 0.03763 0.03127 -0.0275 0.1088 1.0000
14.000 1.5185 0.03898 0.03272 -0.0271 0.1076 1.0000
14.250 1.5287 0.04048 0.03431 -0.0267 0.1058 1.0000
14.500 1.5376 0.04212 0.03603 -0.0263 0.1038 1.0000
14.750 1.5447 0.04397 0.03792 -0.0260 0.1017 1.0000
15.000 1.5477 0.04625 0.04021 -0.0257 0.0994 1.0000
15.250 1.5542 0.04822 0.04227 -0.0255 0.0971 1.0000
15.500 1.5651 0.04984 0.04399 -0.0255 0.0941 1.0000
15.750 1.5713 0.05197 0.04616 -0.0255 0.0904 1.0000
16.000 1.5771 0.05414 0.04839 -0.0255 0.0864 1.0000
16.250 1.5822 0.05646 0.05073 -0.0256 0.0800 1.0000
16.500 1.5837 0.05917 0.05344 -0.0258 0.0703 1.0000
16.750 1.5772 0.06286 0.05710 -0.0261 0.0631 1.0000
17.000 1.5663 0.06716 0.06139 -0.0266 0.0581 1.0000
17.250 1.5583 0.07117 0.06546 -0.0271 0.0552 1.0000
17.500 1.5467 0.07576 0.07008 -0.0279 0.0528 1.0000
17.750 1.5388 0.07998 0.07437 -0.0288 0.0512 1.0000
18.000 1.5308 0.08427 0.07874 -0.0297 0.0497 1.0000
18.250 1.5225 0.08867 0.08321 -0.0308 0.0486 1.0000
18.500 1.5117 0.09354 0.08813 -0.0322 0.0476 1.0000
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