GOE 284 AIRFOIL (goe284-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 284 AIRFOIL (goe284-il) Reynolds number: 500,000 Max Cl/Cd: 103.53 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe284-il-500000.txt Download as CSV file: xf-goe284-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.8685 0.07092 0.06736 -0.0682 1.0000 0.0381
-15.750 -0.9127 0.06002 0.05624 -0.0766 1.0000 0.0380
-15.500 -0.9395 0.05135 0.04737 -0.0841 1.0000 0.0380
-15.250 -0.9544 0.04436 0.04020 -0.0910 1.0000 0.0381
-15.000 -0.9622 0.03916 0.03483 -0.0964 1.0000 0.0382
-14.750 -0.9659 0.03553 0.03106 -0.0994 1.0000 0.0384
-14.500 -0.9671 0.03299 0.02840 -0.1004 1.0000 0.0386
-14.250 -0.9685 0.03116 0.02647 -0.0996 1.0000 0.0388
-14.000 -0.9686 0.02980 0.02502 -0.0978 0.9959 0.0390
-13.750 -0.9467 0.02825 0.02334 -0.0993 0.9872 0.0393
-13.500 -0.9236 0.02689 0.02185 -0.1004 0.9785 0.0397
-13.250 -0.9041 0.02577 0.02061 -0.1004 0.9676 0.0400
-13.000 -0.8890 0.02488 0.01959 -0.0990 0.9549 0.0403
-12.750 -0.8754 0.02394 0.01855 -0.0973 0.9426 0.0406
-12.500 -0.8624 0.02291 0.01747 -0.0954 0.9311 0.0411
-12.250 -0.8470 0.02207 0.01657 -0.0937 0.9198 0.0417
-12.000 -0.8281 0.02131 0.01575 -0.0926 0.9073 0.0422
-11.750 -0.8085 0.02061 0.01497 -0.0914 0.8952 0.0428
-11.500 -0.7882 0.01995 0.01420 -0.0902 0.8823 0.0434
-11.250 -0.7663 0.01932 0.01346 -0.0893 0.8674 0.0440
-11.000 -0.7437 0.01874 0.01276 -0.0885 0.8515 0.0447
-10.750 -0.7214 0.01809 0.01200 -0.0876 0.8340 0.0454
-10.500 -0.6987 0.01747 0.01130 -0.0869 0.8145 0.0464
-10.250 -0.6746 0.01698 0.01069 -0.0863 0.7930 0.0475
-10.000 -0.6498 0.01655 0.01012 -0.0857 0.7705 0.0488
-9.750 -0.6248 0.01613 0.00955 -0.0852 0.7479 0.0504
-9.500 -0.5994 0.01572 0.00905 -0.0848 0.7268 0.0525
-9.250 -0.5732 0.01537 0.00859 -0.0845 0.7074 0.0555
-9.000 -0.5464 0.01508 0.00824 -0.0843 0.6900 0.0602
-8.750 -0.5186 0.01492 0.00802 -0.0842 0.6750 0.0667
-8.500 -0.4897 0.01497 0.00799 -0.0842 0.6619 0.0734
-8.250 -0.4602 0.01513 0.00812 -0.0843 0.6502 0.0781
-8.000 -0.4311 0.01521 0.00811 -0.0844 0.6406 0.0819
-7.750 -0.4017 0.01540 0.00824 -0.0845 0.6316 0.0848
-7.500 -0.3726 0.01555 0.00824 -0.0845 0.6240 0.0876
-7.250 -0.3441 0.01543 0.00809 -0.0846 0.6174 0.0898
-7.000 -0.3153 0.01548 0.00812 -0.0846 0.6109 0.0918
-6.750 -0.2867 0.01555 0.00810 -0.0847 0.6049 0.0939
-6.500 -0.2575 0.01554 0.00802 -0.0847 0.6001 0.0959
-6.250 -0.2287 0.01546 0.00785 -0.0848 0.5954 0.0976
-6.000 -0.2006 0.01518 0.00757 -0.0849 0.5911 0.0996
-5.750 -0.1720 0.01516 0.00751 -0.0849 0.5868 0.1013
-5.500 -0.1430 0.01510 0.00743 -0.0851 0.5834 0.1032
-5.250 -0.1138 0.01503 0.00732 -0.0852 0.5801 0.1051
-5.000 -0.0845 0.01499 0.00721 -0.0853 0.5768 0.1065
-4.750 -0.0561 0.01462 0.00680 -0.0854 0.5737 0.1081
-4.500 -0.0277 0.01435 0.00652 -0.0855 0.5707 0.1100
-4.250 0.0011 0.01425 0.00640 -0.0856 0.5674 0.1116
-4.000 0.0301 0.01417 0.00629 -0.0857 0.5645 0.1134
-3.750 0.0594 0.01405 0.00617 -0.0859 0.5621 0.1153
-3.500 0.0888 0.01398 0.00607 -0.0861 0.5597 0.1171
-3.250 0.1182 0.01393 0.00599 -0.0862 0.5573 0.1183
-3.000 0.1464 0.01347 0.00554 -0.0863 0.5550 0.1206
-2.750 0.1752 0.01328 0.00536 -0.0864 0.5527 0.1221
-2.500 0.2042 0.01316 0.00522 -0.0866 0.5504 0.1236
-2.250 0.2331 0.01312 0.00514 -0.0867 0.5473 0.1251
-2.000 0.2622 0.01302 0.00504 -0.0869 0.5446 0.1269
-1.750 0.2915 0.01290 0.00492 -0.0870 0.5417 0.1287
-1.500 0.3207 0.01281 0.00482 -0.0872 0.5384 0.1302
-1.250 0.3494 0.01260 0.00461 -0.0873 0.5350 0.1323
-1.000 0.3782 0.01245 0.00446 -0.0874 0.5317 0.1351
-0.750 0.4071 0.01244 0.00442 -0.0875 0.5280 0.1378
-0.500 0.4362 0.01239 0.00439 -0.0877 0.5252 0.1407
-0.250 0.4654 0.01232 0.00433 -0.0879 0.5226 0.1437
0.000 0.4944 0.01219 0.00425 -0.0881 0.5196 0.1489
0.250 0.5235 0.01211 0.00420 -0.0883 0.5168 0.1550
0.500 0.5526 0.01204 0.00416 -0.0884 0.5140 0.1633
0.750 0.5815 0.01196 0.00415 -0.0886 0.5113 0.1821
1.000 0.6098 0.01180 0.00423 -0.0889 0.5084 0.2589
1.250 0.6378 0.01153 0.00430 -0.0891 0.5063 0.3583
1.500 0.6644 0.01100 0.00437 -0.0892 0.5038 0.5370
1.750 0.6874 0.01038 0.00449 -0.0881 0.5011 0.7574
2.000 0.7080 0.01010 0.00461 -0.0859 0.4981 0.9059
2.250 0.7480 0.01011 0.00464 -0.0881 0.4947 0.9727
2.500 0.7949 0.01023 0.00469 -0.0920 0.4911 0.9960
2.750 0.8284 0.01036 0.00477 -0.0933 0.4879 1.0000
3.000 0.8541 0.01040 0.00482 -0.0928 0.4849 1.0000
3.250 0.8802 0.01045 0.00486 -0.0925 0.4814 1.0000
3.500 0.9066 0.01051 0.00489 -0.0922 0.4779 1.0000
3.750 0.9332 0.01059 0.00493 -0.0919 0.4742 1.0000
4.000 0.9600 0.01075 0.00502 -0.0917 0.4703 1.0000
4.250 0.9869 0.01078 0.00510 -0.0916 0.4664 1.0000
4.500 1.0139 0.01083 0.00516 -0.0914 0.4618 1.0000
4.750 1.0407 0.01091 0.00520 -0.0912 0.4569 1.0000
5.000 1.0672 0.01103 0.00528 -0.0910 0.4516 1.0000
5.250 1.0942 0.01108 0.00536 -0.0909 0.4449 1.0000
5.500 1.1201 0.01119 0.00542 -0.0906 0.4375 1.0000
5.750 1.1466 0.01129 0.00554 -0.0905 0.4295 1.0000
6.000 1.1719 0.01143 0.00563 -0.0901 0.4202 1.0000
6.250 1.1976 0.01158 0.00578 -0.0898 0.4091 1.0000
6.500 1.2217 0.01180 0.00594 -0.0893 0.3959 1.0000
6.750 1.2444 0.01210 0.00616 -0.0886 0.3809 1.0000
7.000 1.2659 0.01247 0.00645 -0.0877 0.3664 1.0000
7.500 1.3070 0.01331 0.00716 -0.0856 0.3426 1.0000
7.750 1.3265 0.01377 0.00756 -0.0845 0.3335 1.0000
8.000 1.3455 0.01422 0.00798 -0.0832 0.3253 1.0000
8.250 1.3631 0.01469 0.00842 -0.0818 0.3184 1.0000
8.500 1.3801 0.01511 0.00884 -0.0801 0.3125 1.0000
8.750 1.3941 0.01566 0.00936 -0.0781 0.3070 1.0000
9.000 1.4102 0.01618 0.00989 -0.0766 0.3023 1.0000
9.250 1.4283 0.01665 0.01038 -0.0754 0.2981 1.0000
9.500 1.4444 0.01723 0.01097 -0.0740 0.2941 1.0000
9.750 1.4582 0.01795 0.01167 -0.0724 0.2901 1.0000
10.000 1.4739 0.01860 0.01235 -0.0711 0.2865 1.0000
10.250 1.4919 0.01915 0.01295 -0.0702 0.2829 1.0000
10.500 1.5073 0.01986 0.01368 -0.0690 0.2789 1.0000
10.750 1.5205 0.02073 0.01455 -0.0677 0.2753 1.0000
11.000 1.5319 0.02174 0.01555 -0.0663 0.2716 1.0000
11.250 1.5492 0.02242 0.01631 -0.0656 0.2690 1.0000
11.500 1.5645 0.02324 0.01719 -0.0647 0.2653 1.0000
11.750 1.5773 0.02427 0.01824 -0.0637 0.2617 1.0000
12.000 1.5876 0.02548 0.01946 -0.0626 0.2584 1.0000
12.250 1.5981 0.02672 0.02073 -0.0615 0.2554 1.0000
12.500 1.6129 0.02771 0.02180 -0.0609 0.2529 1.0000
12.750 1.6259 0.02884 0.02300 -0.0603 0.2499 1.0000
13.000 1.6361 0.03021 0.02442 -0.0595 0.2465 1.0000
13.250 1.6429 0.03189 0.02611 -0.0586 0.2429 1.0000
13.500 1.6504 0.03354 0.02780 -0.0578 0.2396 1.0000
13.750 1.6620 0.03491 0.02926 -0.0573 0.2365 1.0000
14.000 1.6701 0.03658 0.03100 -0.0567 0.2326 1.0000
14.250 1.6739 0.03869 0.03313 -0.0561 0.2284 1.0000
14.500 1.6777 0.04083 0.03531 -0.0554 0.2247 1.0000
14.750 1.6861 0.04263 0.03720 -0.0551 0.2205 1.0000
15.000 1.6893 0.04492 0.03954 -0.0547 0.2156 1.0000
15.250 1.6878 0.04768 0.04231 -0.0541 0.2108 1.0000
15.500 1.6939 0.04978 0.04451 -0.0538 0.2055 1.0000
15.750 1.6902 0.05290 0.04765 -0.0535 0.1987 1.0000
16.000 1.6887 0.05583 0.05062 -0.0532 0.1895 1.0000
16.250 1.6809 0.05947 0.05426 -0.0529 0.1781 1.0000
16.500 1.6644 0.06417 0.05892 -0.0526 0.1599 1.0000
16.750 1.6333 0.07060 0.06523 -0.0524 0.1381 1.0000
17.000 1.6090 0.07636 0.07094 -0.0524 0.1272 1.0000
17.250 1.5935 0.08117 0.07576 -0.0524 0.1210 1.0000
17.500 1.5795 0.08586 0.08048 -0.0526 0.1168 1.0000
17.750 1.5676 0.09040 0.08506 -0.0529 0.1132 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 284 AIRFOIL (goe284-il)