GOE 284 AIRFOIL (goe284-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 284 AIRFOIL (goe284-il) Reynolds number: 200,000 Max Cl/Cd: 69.48 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe284-il-200000-n5.txt Download as CSV file: xf-goe284-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6436 0.07044 0.06591 -0.0692 1.0000 0.0440
-13.000 -0.7941 0.03666 0.03112 -0.1007 0.9592 0.0435
-12.750 -0.7928 0.03444 0.02869 -0.1005 0.9415 0.0439
-12.500 -0.7864 0.03264 0.02669 -0.0998 0.9259 0.0444
-12.250 -0.7766 0.03127 0.02521 -0.0987 0.9107 0.0450
-12.000 -0.7641 0.03009 0.02394 -0.0976 0.8957 0.0456
-11.750 -0.7499 0.02898 0.02271 -0.0964 0.8807 0.0464
-11.500 -0.7345 0.02793 0.02151 -0.0952 0.8650 0.0472
-11.250 -0.7176 0.02692 0.02034 -0.0941 0.8479 0.0481
-11.000 -0.6996 0.02596 0.01919 -0.0931 0.8301 0.0492
-10.750 -0.6802 0.02518 0.01831 -0.0921 0.8115 0.0502
-10.500 -0.6596 0.02448 0.01747 -0.0912 0.7924 0.0515
-10.250 -0.6381 0.02378 0.01661 -0.0904 0.7735 0.0532
-10.000 -0.6156 0.02319 0.01587 -0.0898 0.7555 0.0552
-9.750 -0.5919 0.02273 0.01530 -0.0892 0.7386 0.0575
-9.500 -0.5677 0.02229 0.01470 -0.0887 0.7228 0.0606
-9.250 -0.5423 0.02200 0.01429 -0.0883 0.7079 0.0641
-9.000 -0.5163 0.02179 0.01397 -0.0880 0.6944 0.0678
-8.750 -0.4904 0.02148 0.01346 -0.0877 0.6825 0.0723
-8.500 -0.4633 0.02147 0.01337 -0.0875 0.6710 0.0754
-8.250 -0.4368 0.02119 0.01285 -0.0873 0.6612 0.0794
-8.000 -0.4095 0.02120 0.01280 -0.0871 0.6514 0.0818
-7.750 -0.3827 0.02104 0.01245 -0.0869 0.6432 0.0849
-7.500 -0.3556 0.02079 0.01202 -0.0868 0.6352 0.0875
-7.250 -0.3283 0.02074 0.01191 -0.0867 0.6282 0.0895
-7.000 -0.3009 0.02061 0.01166 -0.0866 0.6224 0.0919
-6.750 -0.2733 0.02038 0.01124 -0.0865 0.6166 0.0946
-6.500 -0.2459 0.02016 0.01094 -0.0865 0.6112 0.0966
-6.250 -0.2184 0.02007 0.01081 -0.0864 0.6066 0.0987
-6.000 -0.1905 0.01996 0.01062 -0.0864 0.6023 0.1013
-5.750 -0.1624 0.01976 0.01029 -0.0864 0.5979 0.1038
-5.500 -0.1345 0.01952 0.00992 -0.0864 0.5938 0.1058
-5.250 -0.1067 0.01928 0.00969 -0.0864 0.5899 0.1079
-5.000 -0.0788 0.01916 0.00952 -0.0864 0.5863 0.1103
-4.750 -0.0506 0.01900 0.00928 -0.0865 0.5828 0.1128
-4.500 -0.0221 0.01879 0.00899 -0.0865 0.5792 0.1149
-4.250 0.0064 0.01858 0.00869 -0.0866 0.5760 0.1164
-4.000 0.0345 0.01822 0.00832 -0.0866 0.5729 0.1177
-3.750 0.0626 0.01794 0.00803 -0.0867 0.5701 0.1191
-3.500 0.0908 0.01774 0.00780 -0.0867 0.5675 0.1206
-3.250 0.1192 0.01758 0.00759 -0.0867 0.5652 0.1222
-3.000 0.1477 0.01739 0.00739 -0.0868 0.5627 0.1238
-2.750 0.1762 0.01721 0.00721 -0.0869 0.5599 0.1253
-2.500 0.2047 0.01705 0.00704 -0.0869 0.5569 0.1269
-2.250 0.2332 0.01692 0.00688 -0.0870 0.5543 0.1285
-2.000 0.2615 0.01676 0.00673 -0.0871 0.5519 0.1303
-1.750 0.2897 0.01661 0.00660 -0.0871 0.5497 0.1327
-1.500 0.3181 0.01652 0.00650 -0.0872 0.5475 0.1352
-1.250 0.3467 0.01648 0.00642 -0.0873 0.5452 0.1378
-1.000 0.3751 0.01641 0.00637 -0.0874 0.5424 0.1406
-0.750 0.4034 0.01634 0.00632 -0.0874 0.5388 0.1434
-0.500 0.4314 0.01621 0.00624 -0.0875 0.5345 0.1474
-0.250 0.4594 0.01612 0.00616 -0.0875 0.5300 0.1527
0.250 0.5158 0.01602 0.00608 -0.0876 0.5225 0.1680
0.500 0.5438 0.01594 0.00611 -0.0876 0.5189 0.1819
1.000 0.5991 0.01568 0.00619 -0.0877 0.5117 0.2646
1.250 0.6266 0.01553 0.00621 -0.0877 0.5083 0.3261
1.500 0.6535 0.01532 0.00625 -0.0877 0.5052 0.4143
1.750 0.6779 0.01492 0.00642 -0.0872 0.5017 0.5639
2.000 0.6991 0.01449 0.00662 -0.0855 0.4981 0.7411
2.250 0.7279 0.01430 0.00678 -0.0849 0.4942 0.9014
2.500 0.7737 0.01436 0.00682 -0.0884 0.4902 0.9809
2.750 0.8093 0.01449 0.00684 -0.0900 0.4867 1.0000
3.000 0.8345 0.01462 0.00698 -0.0896 0.4825 1.0000
3.250 0.8599 0.01475 0.00711 -0.0892 0.4781 1.0000
3.500 0.8857 0.01488 0.00721 -0.0888 0.4739 1.0000
3.750 0.9117 0.01501 0.00727 -0.0885 0.4700 1.0000
4.000 0.9375 0.01516 0.00739 -0.0882 0.4659 1.0000
4.250 0.9629 0.01532 0.00759 -0.0878 0.4607 1.0000
4.500 0.9884 0.01546 0.00771 -0.0875 0.4555 1.0000
4.750 1.0140 0.01560 0.00779 -0.0871 0.4509 1.0000
5.000 1.0390 0.01578 0.00801 -0.0867 0.4448 1.0000
5.250 1.0637 0.01594 0.00818 -0.0862 0.4382 1.0000
5.500 1.0882 0.01611 0.00830 -0.0857 0.4319 1.0000
5.750 1.1121 0.01631 0.00854 -0.0852 0.4237 1.0000
6.000 1.1354 0.01650 0.00868 -0.0845 0.4161 1.0000
6.250 1.1584 0.01673 0.00893 -0.0838 0.4062 1.0000
6.500 1.1802 0.01699 0.00916 -0.0829 0.3962 1.0000
6.750 1.2006 0.01728 0.00940 -0.0818 0.3853 1.0000
7.000 1.2202 0.01763 0.00971 -0.0807 0.3740 1.0000
7.250 1.2381 0.01805 0.01006 -0.0793 0.3637 1.0000
7.500 1.2543 0.01852 0.01047 -0.0776 0.3541 1.0000
7.750 1.2700 0.01901 0.01094 -0.0759 0.3457 1.0000
8.000 1.2818 0.01959 0.01147 -0.0736 0.3382 1.0000
8.250 1.2953 0.02019 0.01205 -0.0717 0.3313 1.0000
8.500 1.3083 0.02086 0.01271 -0.0699 0.3249 1.0000
8.750 1.3205 0.02162 0.01343 -0.0680 0.3194 1.0000
9.000 1.3356 0.02231 0.01415 -0.0667 0.3144 1.0000
9.250 1.3493 0.02309 0.01493 -0.0653 0.3096 1.0000
9.500 1.3617 0.02396 0.01579 -0.0638 0.3053 1.0000
9.750 1.3755 0.02481 0.01666 -0.0625 0.3015 1.0000
10.000 1.3898 0.02566 0.01756 -0.0614 0.2975 1.0000
10.250 1.4028 0.02660 0.01854 -0.0602 0.2937 1.0000
10.500 1.4151 0.02762 0.01957 -0.0591 0.2902 1.0000
10.750 1.4270 0.02868 0.02062 -0.0579 0.2872 1.0000
11.000 1.4406 0.02969 0.02170 -0.0570 0.2842 1.0000
11.250 1.4534 0.03077 0.02286 -0.0561 0.2810 1.0000
11.500 1.4648 0.03195 0.02410 -0.0552 0.2777 1.0000
11.750 1.4753 0.03322 0.02541 -0.0543 0.2744 1.0000
12.000 1.4855 0.03453 0.02672 -0.0534 0.2714 1.0000
12.250 1.4962 0.03584 0.02809 -0.0526 0.2685 1.0000
12.500 1.5055 0.03732 0.02968 -0.0519 0.2651 1.0000
12.750 1.5137 0.03890 0.03135 -0.0512 0.2616 1.0000
13.000 1.5211 0.04055 0.03305 -0.0504 0.2581 1.0000
13.250 1.5284 0.04220 0.03471 -0.0497 0.2548 1.0000
13.500 1.5356 0.04393 0.03650 -0.0491 0.2517 1.0000
13.750 1.5419 0.04584 0.03855 -0.0486 0.2484 1.0000
14.000 1.5473 0.04785 0.04066 -0.0482 0.2448 1.0000
14.250 1.5512 0.05001 0.04286 -0.0478 0.2408 1.0000
14.500 1.5558 0.05205 0.04490 -0.0473 0.2372 1.0000
14.750 1.5588 0.05448 0.04749 -0.0471 0.2334 1.0000
15.000 1.5600 0.05711 0.05024 -0.0469 0.2288 1.0000
15.250 1.5611 0.05974 0.05291 -0.0467 0.2243 1.0000
15.500 1.5632 0.06223 0.05545 -0.0465 0.2205 1.0000
15.750 1.5629 0.06519 0.05856 -0.0466 0.2159 1.0000
16.000 1.5603 0.06840 0.06185 -0.0466 0.2103 1.0000
16.250 1.5585 0.07151 0.06501 -0.0467 0.2053 1.0000
16.500 1.5542 0.07507 0.06871 -0.0470 0.1989 1.0000
16.750 1.5481 0.07881 0.07248 -0.0473 0.1921 1.0000
17.000 1.5415 0.08276 0.07656 -0.0477 0.1835 1.0000
17.250 1.5311 0.08723 0.08109 -0.0483 0.1725 1.0000
17.500 1.5160 0.09237 0.08625 -0.0491 0.1569 1.0000
17.750 1.4930 0.09864 0.09244 -0.0502 0.1410 1.0000
18.000 1.4682 0.10529 0.09904 -0.0515 0.1312 1.0000
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Polar data table (+)
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