GOE 284 AIRFOIL (goe284-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 284 AIRFOIL (goe284-il) Reynolds number: 100,000 Max Cl/Cd: 45.19 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe284-il-100000-n5.txt Download as CSV file: xf-goe284-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2510 0.09628 0.09084 -0.0623 0.8987 0.0632
-10.500 -0.2699 0.08875 0.08327 -0.0663 0.8807 0.0649
-10.250 -0.2847 0.08240 0.07690 -0.0694 0.8617 0.0662
-10.000 -0.2841 0.07925 0.07370 -0.0703 0.8406 0.0672
-9.750 -0.4862 0.04168 0.03508 -0.0967 0.8281 0.0724
-9.500 -0.4668 0.04135 0.03469 -0.0957 0.8105 0.0736
-9.250 -0.4561 0.03954 0.03262 -0.0950 0.7938 0.0760
-9.000 -0.4512 0.03643 0.02898 -0.0943 0.7790 0.0799
-8.750 -0.4290 0.03621 0.02867 -0.0935 0.7646 0.0821
-8.500 -0.4172 0.03387 0.02576 -0.0928 0.7509 0.0872
-8.250 -0.3922 0.03387 0.02576 -0.0923 0.7385 0.0894
-8.000 -0.3723 0.03277 0.02430 -0.0917 0.7278 0.0936
-7.750 -0.3506 0.03184 0.02311 -0.0914 0.7173 0.0970
-7.500 -0.3260 0.03154 0.02272 -0.0910 0.7081 0.0998
-7.250 -0.3040 0.03055 0.02132 -0.0906 0.6994 0.1043
-7.000 -0.2795 0.02998 0.02062 -0.0903 0.6910 0.1072
-6.750 -0.2539 0.02971 0.02026 -0.0900 0.6839 0.1102
-6.500 -0.2293 0.02920 0.01949 -0.0898 0.6760 0.1151
-6.250 -0.2039 0.02883 0.01903 -0.0896 0.6694 0.1191
-6.000 -0.1776 0.02869 0.01884 -0.0895 0.6638 0.1233
-5.750 -0.1519 0.02814 0.01804 -0.0894 0.6578 0.1276
-5.500 -0.1259 0.02740 0.01705 -0.0893 0.6524 0.1301
-5.250 -0.0992 0.02680 0.01639 -0.0892 0.6479 0.1320
-5.000 -0.0721 0.02629 0.01576 -0.0892 0.6438 0.1340
-4.750 -0.0449 0.02576 0.01515 -0.0892 0.6388 0.1359
-4.500 -0.0176 0.02526 0.01451 -0.0892 0.6341 0.1377
-4.250 0.0099 0.02480 0.01389 -0.0891 0.6298 0.1399
-4.000 0.0378 0.02440 0.01328 -0.0891 0.6262 0.1420
-3.750 0.0656 0.02401 0.01278 -0.0891 0.6225 0.1438
-3.500 0.0931 0.02360 0.01241 -0.0891 0.6185 0.1454
-3.250 0.1208 0.02329 0.01211 -0.0892 0.6149 0.1473
-3.000 0.1486 0.02303 0.01182 -0.0892 0.6116 0.1497
-2.750 0.1766 0.02280 0.01153 -0.0892 0.6085 0.1525
-2.500 0.2048 0.02259 0.01122 -0.0891 0.6056 0.1554
-2.250 0.2324 0.02245 0.01103 -0.0891 0.6022 0.1579
-2.000 0.2593 0.02224 0.01091 -0.0890 0.5985 0.1604
-1.750 0.2865 0.02210 0.01083 -0.0890 0.5954 0.1636
-1.500 0.3139 0.02201 0.01075 -0.0889 0.5923 0.1678
-1.250 0.3416 0.02193 0.01062 -0.0889 0.5893 0.1727
-1.000 0.3693 0.02180 0.01051 -0.0888 0.5866 0.1778
-0.750 0.3968 0.02176 0.01048 -0.0887 0.5839 0.1841
-0.250 0.4491 0.02177 0.01071 -0.0884 0.5763 0.2032
0.000 0.4760 0.02166 0.01069 -0.0882 0.5716 0.2214
0.250 0.5038 0.02147 0.01057 -0.0881 0.5673 0.2538
0.500 0.5307 0.02131 0.01058 -0.0880 0.5628 0.3080
0.750 0.5548 0.02113 0.01079 -0.0877 0.5573 0.3903
1.000 0.5774 0.02066 0.01097 -0.0867 0.5529 0.5581
1.250 0.5986 0.02012 0.01115 -0.0843 0.5492 0.7915
1.500 0.6515 0.02002 0.01108 -0.0883 0.5453 0.9598
1.750 0.6888 0.02031 0.01136 -0.0906 0.5400 1.0000
2.000 0.7115 0.02057 0.01157 -0.0898 0.5351 1.0000
2.250 0.7363 0.02074 0.01163 -0.0892 0.5307 1.0000
2.500 0.7629 0.02086 0.01161 -0.0889 0.5269 1.0000
2.750 0.7871 0.02111 0.01180 -0.0883 0.5226 1.0000
3.000 0.8086 0.02145 0.01216 -0.0875 0.5169 1.0000
3.250 0.8330 0.02166 0.01232 -0.0869 0.5121 1.0000
3.500 0.8598 0.02178 0.01232 -0.0866 0.5079 1.0000
3.750 0.8849 0.02200 0.01249 -0.0862 0.5035 1.0000
4.000 0.9051 0.02241 0.01296 -0.0852 0.4974 1.0000
4.250 0.9293 0.02262 0.01314 -0.0846 0.4922 1.0000
4.500 0.9565 0.02271 0.01313 -0.0844 0.4879 1.0000
4.750 0.9774 0.02308 0.01355 -0.0835 0.4820 1.0000
5.000 0.9982 0.02341 0.01392 -0.0825 0.4755 1.0000
5.250 1.0238 0.02352 0.01396 -0.0821 0.4703 1.0000
5.500 1.0448 0.02384 0.01430 -0.0811 0.4643 1.0000
5.750 1.0637 0.02424 0.01476 -0.0799 0.4571 1.0000
6.000 1.0883 0.02436 0.01483 -0.0794 0.4518 1.0000
6.250 1.1053 0.02485 0.01539 -0.0780 0.4446 1.0000
6.500 1.1244 0.02520 0.01577 -0.0768 0.4376 1.0000
6.750 1.1470 0.02538 0.01591 -0.0760 0.4320 1.0000
7.000 1.1591 0.02607 0.01670 -0.0740 0.4235 1.0000
7.250 1.1802 0.02627 0.01686 -0.0730 0.4175 1.0000
7.500 1.1909 0.02700 0.01768 -0.0709 0.4093 1.0000
7.750 1.2060 0.02739 0.01805 -0.0692 0.4027 1.0000
8.000 1.2166 0.02807 0.01874 -0.0670 0.3957 1.0000
8.250 1.2279 0.02877 0.01946 -0.0651 0.3887 1.0000
8.500 1.2445 0.02924 0.01989 -0.0638 0.3830 1.0000
8.750 1.2510 0.03037 0.02108 -0.0617 0.3757 1.0000
9.000 1.2675 0.03093 0.02158 -0.0605 0.3702 1.0000
9.250 1.2773 0.03200 0.02267 -0.0590 0.3642 1.0000
9.500 1.2865 0.03315 0.02386 -0.0575 0.3583 1.0000
9.750 1.3051 0.03367 0.02430 -0.0566 0.3535 1.0000
10.000 1.3113 0.03515 0.02584 -0.0552 0.3478 1.0000
10.250 1.3194 0.03653 0.02726 -0.0539 0.3424 1.0000
10.500 1.3375 0.03715 0.02784 -0.0531 0.3380 1.0000
10.750 1.3479 0.03846 0.02918 -0.0521 0.3336 1.0000
11.000 1.3515 0.04036 0.03118 -0.0509 0.3289 1.0000
11.250 1.3628 0.04166 0.03251 -0.0501 0.3250 1.0000
11.500 1.3825 0.04225 0.03308 -0.0495 0.3218 1.0000
11.750 1.3966 0.04335 0.03421 -0.0488 0.3185 1.0000
12.000 1.3920 0.04613 0.03715 -0.0477 0.3142 1.0000
12.250 1.3962 0.04815 0.03925 -0.0469 0.3102 1.0000
12.500 1.4109 0.04918 0.04031 -0.0463 0.3067 1.0000
12.750 1.4381 0.04905 0.04011 -0.0459 0.3037 1.0000
13.000 1.4222 0.05309 0.04437 -0.0450 0.2998 1.0000
13.250 1.4109 0.05687 0.04832 -0.0444 0.2958 1.0000
13.500 1.4130 0.05931 0.05085 -0.0439 0.2925 1.0000
13.750 1.4274 0.06043 0.05202 -0.0434 0.2899 1.0000
14.000 1.4525 0.06039 0.05198 -0.0429 0.2876 1.0000
14.250 1.4097 0.06802 0.05988 -0.0429 0.2829 1.0000
14.500 1.3480 0.07871 0.07083 -0.0439 0.2759 1.0000
14.750 1.3739 0.07821 0.07033 -0.0433 0.2732 1.0000
15.000 1.4115 0.07624 0.06835 -0.0425 0.2711 1.0000
15.500 1.2368 0.10754 0.10013 -0.0488 0.2515 1.0000
15.750 1.3007 0.10079 0.09337 -0.0464 0.2526 1.0000
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