GOE 284 AIRFOIL (goe284-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 284 AIRFOIL (goe284-il) Reynolds number: 1,000,000 Max Cl/Cd: 107.08 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe284-il-1000000-n5.txt Download as CSV file: xf-goe284-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 284 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.8108 0.09511 0.09223 -0.0481 1.0000 0.0260
-16.500 -0.8420 0.08673 0.08376 -0.0537 0.9754 0.0260
-16.250 -1.1302 0.03625 0.03227 -0.0937 0.9477 0.0254
-16.000 -1.1459 0.03171 0.02752 -0.0966 0.9328 0.0255
-15.750 -1.1503 0.02938 0.02502 -0.0962 0.9201 0.0256
-15.500 -1.1496 0.02777 0.02329 -0.0946 0.9075 0.0257
-15.250 -1.1435 0.02655 0.02196 -0.0928 0.8961 0.0258
-15.000 -1.1313 0.02546 0.02076 -0.0917 0.8839 0.0259
-14.750 -1.1161 0.02450 0.01970 -0.0907 0.8707 0.0261
-14.500 -1.0990 0.02364 0.01873 -0.0898 0.8564 0.0263
-14.250 -1.0805 0.02287 0.01784 -0.0890 0.8398 0.0265
-14.000 -1.0608 0.02216 0.01701 -0.0882 0.8210 0.0266
-13.750 -1.0401 0.02150 0.01622 -0.0876 0.8006 0.0268
-13.500 -1.0185 0.02089 0.01547 -0.0870 0.7798 0.0270
-13.250 -0.9960 0.02032 0.01477 -0.0864 0.7587 0.0271
-13.000 -0.9730 0.01979 0.01411 -0.0860 0.7378 0.0273
-12.750 -0.9493 0.01929 0.01349 -0.0856 0.7176 0.0275
-12.500 -0.9250 0.01882 0.01290 -0.0852 0.6986 0.0277
-12.250 -0.9003 0.01838 0.01234 -0.0849 0.6810 0.0279
-12.000 -0.8752 0.01797 0.01181 -0.0846 0.6645 0.0280
-11.750 -0.8497 0.01757 0.01131 -0.0843 0.6496 0.0282
-11.500 -0.8237 0.01719 0.01084 -0.0841 0.6368 0.0283
-11.250 -0.7978 0.01681 0.01036 -0.0839 0.6242 0.0285
-11.000 -0.7721 0.01634 0.00981 -0.0836 0.6131 0.0289
-10.750 -0.7459 0.01593 0.00933 -0.0834 0.6027 0.0292
-10.500 -0.7193 0.01555 0.00888 -0.0833 0.5935 0.0295
-10.250 -0.6924 0.01521 0.00847 -0.0831 0.5848 0.0298
-10.000 -0.6651 0.01487 0.00808 -0.0830 0.5786 0.0302
-9.750 -0.6376 0.01456 0.00772 -0.0830 0.5719 0.0306
-9.500 -0.6100 0.01429 0.00737 -0.0829 0.5656 0.0310
-9.250 -0.5820 0.01401 0.00705 -0.0829 0.5610 0.0314
-9.000 -0.5539 0.01376 0.00676 -0.0828 0.5562 0.0318
-8.750 -0.5257 0.01350 0.00645 -0.0828 0.5513 0.0324
-8.500 -0.4978 0.01322 0.00612 -0.0828 0.5466 0.0331
-8.250 -0.4695 0.01295 0.00582 -0.0828 0.5431 0.0339
-8.000 -0.4410 0.01270 0.00555 -0.0828 0.5399 0.0349
-7.750 -0.4124 0.01247 0.00529 -0.0829 0.5366 0.0359
-7.500 -0.3839 0.01221 0.00501 -0.0829 0.5333 0.0378
-7.250 -0.3555 0.01195 0.00473 -0.0830 0.5299 0.0409
-7.000 -0.3278 0.01157 0.00440 -0.0830 0.5263 0.0512
-6.750 -0.2992 0.01132 0.00421 -0.0831 0.5237 0.0638
-6.500 -0.2699 0.01118 0.00410 -0.0832 0.5214 0.0691
-6.250 -0.2404 0.01108 0.00399 -0.0834 0.5191 0.0724
-6.000 -0.2109 0.01099 0.00390 -0.0835 0.5168 0.0752
-5.750 -0.1813 0.01091 0.00380 -0.0837 0.5145 0.0773
-5.500 -0.1517 0.01084 0.00371 -0.0839 0.5122 0.0791
-5.250 -0.1222 0.01076 0.00363 -0.0840 0.5098 0.0812
-5.000 -0.0926 0.01071 0.00356 -0.0842 0.5074 0.0829
-4.750 -0.0630 0.01065 0.00349 -0.0844 0.5052 0.0843
-4.500 -0.0332 0.01058 0.00341 -0.0846 0.5041 0.0856
-4.250 -0.0034 0.01052 0.00334 -0.0848 0.5028 0.0865
-4.000 0.0263 0.01043 0.00325 -0.0850 0.5012 0.0876
-3.750 0.0560 0.01034 0.00317 -0.0852 0.4994 0.0888
-3.500 0.0857 0.01028 0.00310 -0.0854 0.4975 0.0900
-3.250 0.1155 0.01023 0.00305 -0.0857 0.4955 0.0916
-3.000 0.1452 0.01019 0.00300 -0.0859 0.4930 0.0930
-2.750 0.1748 0.01016 0.00295 -0.0861 0.4901 0.0941
-2.500 0.2043 0.01016 0.00291 -0.0863 0.4866 0.0949
-2.250 0.2342 0.01010 0.00285 -0.0866 0.4848 0.0959
-2.000 0.2639 0.01001 0.00279 -0.0868 0.4825 0.0980
-1.750 0.2937 0.00996 0.00275 -0.0871 0.4799 0.0997
-1.500 0.3234 0.00992 0.00271 -0.0873 0.4765 0.1011
-1.250 0.3529 0.00990 0.00267 -0.0875 0.4724 0.1023
-1.000 0.3823 0.00991 0.00264 -0.0877 0.4679 0.1034
-0.750 0.4122 0.00987 0.00261 -0.0880 0.4657 0.1045
-0.500 0.4420 0.00985 0.00259 -0.0883 0.4634 0.1053
-0.250 0.4716 0.00980 0.00257 -0.0886 0.4611 0.1073
0.000 0.5012 0.00977 0.00255 -0.0888 0.4587 0.1096
0.250 0.5308 0.00976 0.00255 -0.0891 0.4561 0.1118
0.500 0.5602 0.00976 0.00255 -0.0893 0.4533 0.1138
0.750 0.5895 0.00978 0.00256 -0.0895 0.4504 0.1157
1.000 0.6192 0.00976 0.00257 -0.0898 0.4481 0.1184
1.250 0.6488 0.00974 0.00258 -0.0901 0.4450 0.1226
1.500 0.6782 0.00974 0.00260 -0.0904 0.4409 0.1272
1.750 0.7073 0.00975 0.00262 -0.0906 0.4365 0.1352
2.000 0.7362 0.00975 0.00266 -0.0908 0.4324 0.1491
2.250 0.7654 0.00969 0.00270 -0.0911 0.4285 0.1793
2.500 0.7943 0.00962 0.00275 -0.0914 0.4230 0.2285
2.750 0.8226 0.00961 0.00282 -0.0916 0.4166 0.2688
3.000 0.8515 0.00959 0.00289 -0.0918 0.4099 0.3048
3.500 0.9061 0.00956 0.00312 -0.0920 0.3834 0.4506
3.750 0.9314 0.00948 0.00332 -0.0918 0.3634 0.5972
4.000 0.9552 0.00943 0.00358 -0.0913 0.3440 0.7440
4.250 0.9745 0.00934 0.00385 -0.0895 0.3298 0.8967
4.500 1.0027 0.00953 0.00408 -0.0895 0.3174 0.9796
4.750 1.0371 0.00977 0.00427 -0.0911 0.3078 1.0000
5.000 1.0629 0.01000 0.00445 -0.0908 0.3010 1.0000
5.250 1.0891 0.01021 0.00462 -0.0906 0.2949 1.0000
5.500 1.1145 0.01046 0.00482 -0.0903 0.2885 1.0000
5.750 1.1405 0.01067 0.00500 -0.0901 0.2836 1.0000
6.000 1.1661 0.01089 0.00520 -0.0899 0.2776 1.0000
6.500 1.2160 0.01141 0.00565 -0.0892 0.2658 1.0000
6.750 1.2412 0.01164 0.00586 -0.0888 0.2614 1.0000
7.000 1.2653 0.01191 0.00610 -0.0884 0.2568 1.0000
7.250 1.2894 0.01218 0.00635 -0.0879 0.2528 1.0000
7.500 1.3141 0.01239 0.00657 -0.0876 0.2500 1.0000
7.750 1.3381 0.01264 0.00681 -0.0871 0.2469 1.0000
8.000 1.3610 0.01292 0.00709 -0.0864 0.2432 1.0000
8.250 1.3821 0.01326 0.00740 -0.0855 0.2389 1.0000
8.500 1.4032 0.01356 0.00771 -0.0846 0.2349 1.0000
8.750 1.4222 0.01388 0.00802 -0.0833 0.2309 1.0000
9.000 1.4402 0.01426 0.00839 -0.0819 0.2272 1.0000
9.250 1.4581 0.01468 0.00882 -0.0806 0.2241 1.0000
9.500 1.4761 0.01512 0.00927 -0.0793 0.2209 1.0000
9.750 1.4955 0.01553 0.00969 -0.0784 0.2185 1.0000
10.000 1.5137 0.01601 0.01018 -0.0773 0.2149 1.0000
10.250 1.5296 0.01663 0.01079 -0.0760 0.2103 1.0000
10.500 1.5447 0.01732 0.01148 -0.0747 0.2060 1.0000
10.750 1.5624 0.01789 0.01208 -0.0738 0.2031 1.0000
11.000 1.5781 0.01860 0.01280 -0.0727 0.1987 1.0000
11.250 1.5899 0.01958 0.01377 -0.0713 0.1931 1.0000
11.500 1.6041 0.02045 0.01465 -0.0703 0.1881 1.0000
11.750 1.6127 0.02174 0.01592 -0.0688 0.1796 1.0000
12.000 1.6158 0.02350 0.01762 -0.0671 0.1647 1.0000
12.250 1.5880 0.02785 0.02177 -0.0637 0.1268 1.0000
12.500 1.5775 0.03112 0.02500 -0.0619 0.1135 1.0000
12.750 1.5790 0.03343 0.02734 -0.0610 0.1087 1.0000
13.000 1.5821 0.03567 0.02961 -0.0602 0.1056 1.0000
13.250 1.5839 0.03805 0.03202 -0.0594 0.1026 1.0000
13.500 1.5878 0.04027 0.03429 -0.0588 0.1004 1.0000
13.750 1.5927 0.04242 0.03649 -0.0583 0.0987 1.0000
14.000 1.5962 0.04474 0.03886 -0.0578 0.0969 1.0000
14.250 1.5972 0.04734 0.04150 -0.0573 0.0949 1.0000
14.500 1.5970 0.05008 0.04428 -0.0568 0.0926 1.0000
14.750 1.5991 0.05259 0.04684 -0.0564 0.0908 1.0000
15.000 1.6028 0.05499 0.04930 -0.0561 0.0896 1.0000
15.250 1.6067 0.05734 0.05170 -0.0558 0.0882 1.0000
15.500 1.6081 0.06002 0.05443 -0.0556 0.0867 1.0000
15.750 1.6093 0.06270 0.05716 -0.0553 0.0849 1.0000
16.000 1.6076 0.06578 0.06027 -0.0552 0.0829 1.0000
16.250 1.6091 0.06846 0.06300 -0.0550 0.0811 1.0000
16.500 1.6099 0.07128 0.06588 -0.0549 0.0791 1.0000
16.750 1.6110 0.07405 0.06868 -0.0548 0.0768 1.0000
17.000 1.6072 0.07747 0.07214 -0.0549 0.0744 1.0000
17.250 1.6075 0.08038 0.07509 -0.0549 0.0717 1.0000
17.500 1.6020 0.08405 0.07879 -0.0550 0.0677 1.0000
17.750 1.5976 0.08757 0.08233 -0.0552 0.0630 1.0000
18.000 1.5874 0.09192 0.08670 -0.0555 0.0577 1.0000
18.250 1.5750 0.09661 0.09139 -0.0560 0.0509 1.0000
18.500 1.5585 0.10187 0.09666 -0.0567 0.0438 1.0000
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