GOE 298 AIRFOIL (goe298-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 298 AIRFOIL (goe298-il) Reynolds number: 500,000 Max Cl/Cd: 88.68 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe298-il-500000-n5.txt Download as CSV file: xf-goe298-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 298 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.5288 0.17329 0.17054 0.0121 1.0000 0.0267
-13.250 -1.0104 0.03230 0.02830 -0.0870 1.0000 0.0402
-13.000 -0.9965 0.02927 0.02503 -0.0885 1.0000 0.0408
-12.750 -0.9783 0.02722 0.02280 -0.0892 1.0000 0.0413
-12.500 -0.9573 0.02559 0.02099 -0.0897 0.9961 0.0417
-12.250 -0.9279 0.02420 0.01946 -0.0915 0.9644 0.0423
-12.000 -0.8990 0.02317 0.01833 -0.0926 0.9417 0.0428
-11.750 -0.8739 0.02232 0.01737 -0.0927 0.9259 0.0434
-11.500 -0.8498 0.02155 0.01648 -0.0925 0.9137 0.0439
-11.000 -0.8006 0.02012 0.01478 -0.0920 0.8926 0.0452
-10.750 -0.7755 0.01945 0.01396 -0.0917 0.8824 0.0459
-10.500 -0.7497 0.01881 0.01317 -0.0915 0.8727 0.0466
-10.250 -0.7235 0.01825 0.01256 -0.0913 0.8644 0.0474
-10.000 -0.6969 0.01777 0.01202 -0.0912 0.8542 0.0482
-9.750 -0.6699 0.01732 0.01148 -0.0910 0.8445 0.0490
-9.500 -0.6428 0.01686 0.01092 -0.0909 0.8347 0.0500
-9.250 -0.6154 0.01640 0.01035 -0.0907 0.8246 0.0509
-9.000 -0.5880 0.01596 0.00978 -0.0906 0.8138 0.0517
-8.750 -0.5602 0.01557 0.00935 -0.0905 0.8021 0.0526
-8.500 -0.5324 0.01524 0.00895 -0.0904 0.7909 0.0536
-8.250 -0.5044 0.01492 0.00854 -0.0902 0.7795 0.0546
-8.000 -0.4761 0.01461 0.00812 -0.0901 0.7694 0.0558
-7.750 -0.4478 0.01431 0.00769 -0.0900 0.7596 0.0569
-7.500 -0.4193 0.01404 0.00739 -0.0900 0.7510 0.0581
-7.250 -0.3906 0.01382 0.00713 -0.0899 0.7422 0.0593
-7.000 -0.3619 0.01360 0.00683 -0.0899 0.7345 0.0606
-6.750 -0.3330 0.01335 0.00650 -0.0898 0.7265 0.0620
-6.500 -0.3042 0.01313 0.00620 -0.0898 0.7189 0.0632
-6.250 -0.2750 0.01297 0.00602 -0.0898 0.7116 0.0645
-6.000 -0.2460 0.01284 0.00584 -0.0897 0.7021 0.0660
-5.750 -0.2169 0.01267 0.00560 -0.0897 0.6930 0.0676
-5.500 -0.1877 0.01249 0.00533 -0.0897 0.6838 0.0691
-5.250 -0.1585 0.01239 0.00522 -0.0897 0.6760 0.0705
-5.000 -0.1291 0.01229 0.00510 -0.0897 0.6668 0.0720
-4.750 -0.0999 0.01219 0.00493 -0.0896 0.6580 0.0737
-4.500 -0.0704 0.01204 0.00472 -0.0897 0.6490 0.0753
-4.250 -0.0411 0.01195 0.00460 -0.0897 0.6384 0.0768
-4.000 -0.0117 0.01190 0.00453 -0.0896 0.6256 0.0782
-3.750 0.0177 0.01185 0.00442 -0.0896 0.6135 0.0798
-3.500 0.0469 0.01178 0.00426 -0.0896 0.6011 0.0815
-3.250 0.0763 0.01170 0.00410 -0.0896 0.5903 0.0830
-3.000 0.1056 0.01163 0.00403 -0.0896 0.5810 0.0844
-2.750 0.1350 0.01160 0.00396 -0.0896 0.5724 0.0858
-2.250 0.1937 0.01152 0.00380 -0.0896 0.5570 0.0890
-2.000 0.2230 0.01151 0.00371 -0.0896 0.5484 0.0905
-1.750 0.2523 0.01143 0.00360 -0.0896 0.5411 0.0918
-1.500 0.2817 0.01135 0.00353 -0.0897 0.5354 0.0932
-1.250 0.3110 0.01133 0.00350 -0.0897 0.5302 0.0947
-0.750 0.3698 0.01126 0.00340 -0.0898 0.5209 0.0978
-0.500 0.3992 0.01122 0.00335 -0.0898 0.5156 0.0992
-0.250 0.4284 0.01123 0.00332 -0.0898 0.5093 0.1004
0.000 0.4576 0.01113 0.00323 -0.0898 0.5031 0.1021
0.250 0.4871 0.01107 0.00320 -0.0899 0.4975 0.1037
0.500 0.5164 0.01105 0.00319 -0.0899 0.4913 0.1053
0.750 0.5454 0.01106 0.00318 -0.0899 0.4848 0.1068
1.000 0.5748 0.01103 0.00316 -0.0900 0.4755 0.1083
1.250 0.6037 0.01106 0.00315 -0.0899 0.4608 0.1098
1.500 0.6325 0.01112 0.00315 -0.0899 0.4403 0.1109
1.750 0.6591 0.01140 0.00316 -0.0897 0.3735 0.1127
2.000 0.6854 0.01180 0.00334 -0.0895 0.3328 0.1145
2.250 0.7131 0.01201 0.00348 -0.0893 0.3177 0.1165
2.500 0.7409 0.01219 0.00362 -0.0892 0.3074 0.1186
2.750 0.7692 0.01230 0.00372 -0.0892 0.2999 0.1206
3.000 0.7972 0.01245 0.00385 -0.0891 0.2920 0.1224
3.250 0.8252 0.01260 0.00398 -0.0890 0.2852 0.1249
3.500 0.8536 0.01267 0.00409 -0.0889 0.2801 0.1287
3.750 0.8816 0.01279 0.00422 -0.0888 0.2745 0.1335
4.000 0.9093 0.01294 0.00438 -0.0887 0.2692 0.1403
4.500 0.9655 0.01307 0.00470 -0.0886 0.2605 0.1960
4.750 0.9936 0.01304 0.00492 -0.0887 0.2553 0.3054
5.000 1.0215 0.01255 0.00522 -0.0892 0.2498 0.6558
5.250 1.0388 0.01200 0.00536 -0.0864 0.2456 1.0000
5.500 1.0663 0.01220 0.00553 -0.0862 0.2392 1.0000
5.750 1.0931 0.01247 0.00573 -0.0860 0.2320 1.0000
6.000 1.1203 0.01269 0.00593 -0.0858 0.2254 1.0000
6.250 1.1468 0.01296 0.00615 -0.0855 0.2171 1.0000
6.500 1.1732 0.01323 0.00638 -0.0852 0.2088 1.0000
6.750 1.1988 0.01358 0.00665 -0.0848 0.1977 1.0000
7.000 1.2236 0.01397 0.00695 -0.0844 0.1845 1.0000
7.250 1.2478 0.01440 0.00729 -0.0838 0.1709 1.0000
7.500 1.2715 0.01485 0.00767 -0.0832 0.1588 1.0000
7.750 1.2949 0.01531 0.00806 -0.0825 0.1488 1.0000
8.000 1.3176 0.01581 0.00849 -0.0818 0.1401 1.0000
8.250 1.3401 0.01629 0.00893 -0.0810 0.1332 1.0000
8.500 1.3628 0.01673 0.00935 -0.0803 0.1286 1.0000
8.750 1.3852 0.01716 0.00977 -0.0795 0.1250 1.0000
9.000 1.4066 0.01764 0.01024 -0.0785 0.1217 1.0000
9.250 1.4273 0.01815 0.01074 -0.0775 0.1187 1.0000
9.500 1.4484 0.01858 0.01119 -0.0765 0.1165 1.0000
9.750 1.4682 0.01907 0.01170 -0.0754 0.1140 1.0000
10.000 1.4863 0.01961 0.01225 -0.0740 0.1116 1.0000
10.250 1.5013 0.02019 0.01284 -0.0721 0.1096 1.0000
10.500 1.5155 0.02087 0.01353 -0.0703 0.1079 1.0000
10.750 1.5317 0.02147 0.01419 -0.0688 0.1067 1.0000
11.000 1.5476 0.02214 0.01490 -0.0674 0.1054 1.0000
11.250 1.5629 0.02288 0.01569 -0.0661 0.1041 1.0000
11.500 1.5775 0.02371 0.01656 -0.0648 0.1026 1.0000
11.750 1.5913 0.02463 0.01752 -0.0635 0.1009 1.0000
12.000 1.6036 0.02570 0.01860 -0.0623 0.0990 1.0000
12.250 1.6152 0.02686 0.01979 -0.0610 0.0972 1.0000
12.500 1.6298 0.02781 0.02081 -0.0601 0.0959 1.0000
12.750 1.6432 0.02888 0.02194 -0.0591 0.0945 1.0000
13.000 1.6556 0.03006 0.02317 -0.0582 0.0929 1.0000
13.250 1.6669 0.03137 0.02453 -0.0573 0.0913 1.0000
13.500 1.6769 0.03282 0.02603 -0.0564 0.0897 1.0000
13.750 1.6852 0.03446 0.02771 -0.0555 0.0880 1.0000
14.000 1.6966 0.03584 0.02916 -0.0548 0.0863 1.0000
14.250 1.7066 0.03737 0.03075 -0.0541 0.0842 1.0000
14.500 1.7145 0.03911 0.03254 -0.0535 0.0817 1.0000
14.750 1.7200 0.04112 0.03459 -0.0528 0.0793 1.0000
15.000 1.7279 0.04291 0.03644 -0.0522 0.0764 1.0000
15.250 1.7324 0.04506 0.03862 -0.0516 0.0725 1.0000
15.500 1.7349 0.04744 0.04104 -0.0511 0.0672 1.0000
15.750 1.7321 0.05046 0.04405 -0.0507 0.0587 1.0000
16.000 1.7176 0.05494 0.04847 -0.0505 0.0458 1.0000
16.250 1.7060 0.05927 0.05283 -0.0505 0.0407 1.0000
16.500 1.6970 0.06344 0.05706 -0.0508 0.0379 1.0000
16.750 1.6901 0.06743 0.06113 -0.0511 0.0364 1.0000
17.000 1.6827 0.07158 0.06537 -0.0516 0.0353 1.0000
17.250 1.6738 0.07601 0.06990 -0.0523 0.0343 1.0000
17.500 1.6637 0.08067 0.07466 -0.0531 0.0335 1.0000
17.750 1.6548 0.08522 0.07932 -0.0540 0.0329 1.0000
18.000 1.6445 0.09009 0.08430 -0.0551 0.0324 1.0000
18.250 1.6326 0.09530 0.08963 -0.0565 0.0319 1.0000
18.500 1.6190 0.10086 0.09531 -0.0581 0.0315 1.0000
18.750 1.6039 0.10681 0.10138 -0.0601 0.0312 1.0000
19.000 1.5882 0.11299 0.10769 -0.0623 0.0308 1.0000
19.250 1.5713 0.11950 0.11433 -0.0649 0.0305 1.0000
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