GOE 437 AIRFOIL (goe437-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 437 AIRFOIL (goe437-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.68 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe437-il-1000000-n5.txt Download as CSV file: xf-goe437-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 437 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3210 0.10804 0.10644 -0.0265 1.0000 0.0036
-9.250 -0.3178 0.10523 0.10365 -0.0267 1.0000 0.0036
-9.000 -0.3163 0.10258 0.10102 -0.0266 1.0000 0.0039
-8.750 -0.3040 0.09827 0.09672 -0.0303 0.9987 0.0038
-8.500 -0.2904 0.09609 0.09453 -0.0324 0.9950 0.0046
-8.250 -0.2788 0.09265 0.09110 -0.0352 0.9910 0.0046
-8.000 -0.2666 0.08881 0.08726 -0.0386 0.9859 0.0045
-7.750 -0.2510 0.08498 0.08343 -0.0430 0.9796 0.0057
-7.500 -0.2349 0.08098 0.07944 -0.0477 0.9727 0.0058
-7.250 -0.1265 0.05281 0.05122 -0.0639 0.9233 0.0035
-7.000 -0.1908 0.07015 0.06857 -0.0630 0.9573 0.0035
-6.750 -0.1632 0.06511 0.06349 -0.0717 0.9446 0.0033
-6.500 -0.1386 0.06067 0.05898 -0.0788 0.9256 0.0032
-6.250 -0.1205 0.05604 0.05423 -0.0843 0.8937 0.0032
-6.000 -0.1048 0.05205 0.05005 -0.0880 0.8562 0.0031
-5.500 -0.0759 0.01639 0.01280 -0.1072 0.8032 0.0031
-5.250 -0.0535 0.01377 0.00962 -0.1068 0.7864 0.0033
-5.000 -0.0290 0.01243 0.00789 -0.1063 0.7730 0.0034
-4.750 -0.0036 0.01156 0.00675 -0.1059 0.7611 0.0036
-4.500 0.0215 0.01048 0.00536 -0.1055 0.7488 0.0038
-4.250 0.0472 0.00994 0.00464 -0.1051 0.7350 0.0041
-4.000 0.0734 0.00970 0.00430 -0.1047 0.7207 0.0045
-3.750 0.0998 0.00936 0.00381 -0.1044 0.7087 0.0049
-3.500 0.1263 0.00894 0.00324 -0.1040 0.6988 0.0054
-3.250 0.1531 0.00864 0.00281 -0.1037 0.6889 0.0058
-3.000 0.1798 0.00824 0.00229 -0.1034 0.6794 0.0065
-2.750 0.2066 0.00802 0.00198 -0.1031 0.6680 0.0077
-2.500 0.2334 0.00789 0.00177 -0.1028 0.6537 0.0090
-2.250 0.2600 0.00775 0.00151 -0.1025 0.6360 0.0112
-2.000 0.2863 0.00766 0.00133 -0.1021 0.6129 0.0160
-1.750 0.3120 0.00765 0.00122 -0.1016 0.5820 0.0288
-1.500 0.3379 0.00768 0.00116 -0.1013 0.5566 0.0368
-1.250 0.3643 0.00770 0.00109 -0.1009 0.5382 0.0437
-1.000 0.3910 0.00771 0.00103 -0.1007 0.5257 0.0499
-0.750 0.4177 0.00769 0.00099 -0.1005 0.5157 0.0625
-0.500 0.4447 0.00765 0.00099 -0.1003 0.5070 0.0884
-0.250 0.4717 0.00767 0.00098 -0.1001 0.4987 0.0974
0.000 0.4987 0.00771 0.00098 -0.1000 0.4898 0.1037
0.250 0.5258 0.00773 0.00097 -0.0998 0.4821 0.1086
0.500 0.5528 0.00776 0.00098 -0.0996 0.4745 0.1143
0.750 0.5800 0.00778 0.00099 -0.0995 0.4675 0.1218
1.000 0.6069 0.00781 0.00101 -0.0993 0.4596 0.1300
1.250 0.6339 0.00782 0.00105 -0.0992 0.4518 0.1453
1.500 0.6604 0.00779 0.00111 -0.0990 0.4423 0.1969
1.750 0.6869 0.00776 0.00117 -0.0988 0.4322 0.2528
2.000 0.7109 0.00726 0.00133 -0.0984 0.4234 0.5535
2.500 0.7744 0.00658 0.00153 -0.1005 0.4018 1.0000
2.750 0.8006 0.00670 0.00161 -0.1002 0.3907 1.0000
3.000 0.8265 0.00684 0.00172 -0.0998 0.3794 1.0000
3.250 0.8525 0.00699 0.00182 -0.0995 0.3691 1.0000
3.500 0.8784 0.00714 0.00193 -0.0992 0.3594 1.0000
3.750 0.9041 0.00731 0.00207 -0.0988 0.3476 1.0000
4.000 0.9291 0.00754 0.00223 -0.0983 0.3301 1.0000
4.250 0.9536 0.00782 0.00241 -0.0978 0.3069 1.0000
4.500 0.9781 0.00811 0.00260 -0.0973 0.2857 1.0000
4.750 1.0020 0.00845 0.00282 -0.0967 0.2571 1.0000
5.000 1.0195 0.00945 0.00334 -0.0951 0.1652 1.0000
5.250 1.0309 0.01115 0.00435 -0.0926 0.0306 1.0000
5.500 1.0539 0.01160 0.00474 -0.0919 0.0124 1.0000
5.750 1.0781 0.01191 0.00509 -0.0913 0.0085 1.0000
6.000 1.1017 0.01227 0.00545 -0.0906 0.0066 1.0000
6.250 1.1251 0.01265 0.00588 -0.0899 0.0055 1.0000
6.500 1.1484 0.01302 0.00629 -0.0892 0.0048 1.0000
6.750 1.1711 0.01343 0.00672 -0.0884 0.0041 1.0000
7.000 1.1931 0.01391 0.00725 -0.0875 0.0035 1.0000
7.250 1.2150 0.01438 0.00780 -0.0866 0.0032 1.0000
7.500 1.2363 0.01489 0.00837 -0.0856 0.0029 1.0000
7.750 1.2572 0.01540 0.00893 -0.0845 0.0027 1.0000
8.000 1.2769 0.01601 0.00959 -0.0833 0.0024 1.0000
8.250 1.2921 0.01699 0.01068 -0.0813 0.0022 1.0000
8.500 1.3100 0.01767 0.01144 -0.0798 0.0021 1.0000
8.750 1.3251 0.01853 0.01240 -0.0778 0.0020 1.0000
9.000 1.3382 0.01948 0.01346 -0.0756 0.0019 1.0000
9.250 1.3505 0.02041 0.01449 -0.0732 0.0017 1.0000
9.500 1.3630 0.02112 0.01527 -0.0709 0.0016 1.0000
9.750 1.3707 0.02204 0.01628 -0.0678 0.0016 1.0000
10.000 1.3814 0.02279 0.01713 -0.0654 0.0014 1.0000
10.250 1.3878 0.02384 0.01828 -0.0625 0.0014 1.0000
10.500 1.3961 0.02482 0.01934 -0.0600 0.0013 1.0000
10.750 1.4018 0.02603 0.02065 -0.0574 0.0013 1.0000
11.000 1.4038 0.02760 0.02233 -0.0546 0.0013 1.0000
11.250 1.4045 0.02939 0.02425 -0.0520 0.0012 1.0000
11.500 1.4001 0.03183 0.02686 -0.0492 0.0012 1.0000
11.750 1.3971 0.03437 0.02956 -0.0469 0.0011 1.0000
12.000 1.3999 0.03641 0.03174 -0.0454 0.0011 1.0000
12.250 1.4010 0.03874 0.03422 -0.0441 0.0011 1.0000
12.500 1.3979 0.04170 0.03736 -0.0427 0.0011 1.0000
12.750 1.3894 0.04558 0.04146 -0.0414 0.0011 1.0000
13.000 1.3850 0.04900 0.04506 -0.0407 0.0010 1.0000
13.250 1.3732 0.05377 0.05009 -0.0399 0.0010 1.0000
13.500 1.3557 0.05960 0.05620 -0.0397 0.0010 1.0000
13.750 1.3220 0.06883 0.06581 -0.0401 0.0009 1.0000
14.000 1.2920 0.07780 0.07508 -0.0420 0.0008 1.0000
14.250 1.2733 0.08470 0.08215 -0.0449 0.0008 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 437 AIRFOIL (goe437-il)