GOE 493 AIRFOIL (goe493-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 493 AIRFOIL (goe493-il) Reynolds number: 100,000 Max Cl/Cd: 51.38 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe493-il-100000-n5.txt Download as CSV file: xf-goe493-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 493 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
------ -------- --------- --------- -------- -------- --------
-13.250 -0.5868 0.07968 0.07418 -0.0763 1.0000 0.0338
-13.000 -0.6325 0.06984 0.06418 -0.0814 1.0000 0.0332
-12.750 -0.6644 0.06356 0.05776 -0.0838 1.0000 0.0330
-12.500 -0.6911 0.05891 0.05299 -0.0845 1.0000 0.0329
-12.250 -0.7160 0.05522 0.04922 -0.0841 1.0000 0.0329
-12.000 -0.7404 0.05222 0.04612 -0.0827 1.0000 0.0330
-11.750 -0.7650 0.04975 0.04355 -0.0804 1.0000 0.0330
-11.500 -0.7906 0.04778 0.04150 -0.0770 1.0000 0.0330
-11.250 -0.7903 0.04499 0.03847 -0.0786 0.9942 0.0338
-11.000 -0.7852 0.04247 0.03568 -0.0793 0.9874 0.0349
-10.750 -0.7739 0.04007 0.03293 -0.0802 0.9815 0.0363
-10.500 -0.7592 0.03826 0.03106 -0.0810 0.9756 0.0381
-10.250 -0.7427 0.03665 0.02932 -0.0815 0.9701 0.0402
-10.000 -0.7257 0.03499 0.02741 -0.0817 0.9642 0.0428
-9.750 -0.7027 0.03337 0.02568 -0.0829 0.9603 0.0454
-9.500 -0.6895 0.03224 0.02445 -0.0818 0.9531 0.0487
-9.250 -0.6662 0.03092 0.02297 -0.0825 0.9486 0.0532
-9.000 -0.6449 0.02989 0.02185 -0.0826 0.9436 0.0584
-8.750 -0.6265 0.02891 0.02079 -0.0820 0.9373 0.0640
-8.500 -0.5992 0.02801 0.01973 -0.0829 0.9333 0.0725
-8.250 -0.5740 0.02728 0.01893 -0.0833 0.9289 0.0812
-8.000 -0.5557 0.02667 0.01827 -0.0823 0.9221 0.0893
-7.750 -0.5271 0.02602 0.01751 -0.0832 0.9181 0.1003
-7.500 -0.4944 0.02538 0.01672 -0.0847 0.9154 0.1121
-7.250 -0.4797 0.02498 0.01627 -0.0828 0.9074 0.1203
-7.000 -0.4514 0.02440 0.01562 -0.0834 0.9031 0.1303
-6.750 -0.4184 0.02384 0.01494 -0.0848 0.9003 0.1418
-6.500 -0.3994 0.02347 0.01452 -0.0835 0.8935 0.1510
-6.250 -0.3732 0.02298 0.01400 -0.0835 0.8884 0.1613
-6.000 -0.3406 0.02246 0.01341 -0.0847 0.8853 0.1735
-5.750 -0.3052 0.02193 0.01282 -0.0865 0.8830 0.1872
-5.500 -0.2934 0.02167 0.01257 -0.0837 0.8736 0.1969
-5.250 -0.2618 0.02119 0.01208 -0.0846 0.8701 0.2121
-5.000 -0.2270 0.02068 0.01156 -0.0861 0.8675 0.2311
-4.750 -0.2134 0.02047 0.01138 -0.0836 0.8586 0.2465
-4.500 -0.1831 0.02004 0.01101 -0.0843 0.8547 0.2706
-4.250 -0.1494 0.01960 0.01062 -0.0855 0.8519 0.3004
-4.000 -0.1345 0.01947 0.01055 -0.0832 0.8432 0.3252
-3.750 -0.1048 0.01916 0.01031 -0.0836 0.8389 0.3581
-3.500 -0.0710 0.01884 0.01003 -0.0847 0.8361 0.3924
-3.250 -0.0555 0.01884 0.01007 -0.0824 0.8273 0.4174
-3.000 -0.0252 0.01864 0.00989 -0.0827 0.8230 0.4469
-2.750 0.0091 0.01841 0.00965 -0.0838 0.8201 0.4748
-2.500 0.0245 0.01848 0.00974 -0.0814 0.8111 0.4962
-2.250 0.0551 0.01831 0.00959 -0.0818 0.8069 0.5206
-2.000 0.0899 0.01809 0.00935 -0.0829 0.8040 0.5460
-1.750 0.1043 0.01820 0.00950 -0.0803 0.7946 0.5647
-1.500 0.1360 0.01801 0.00933 -0.0808 0.7906 0.5864
-1.250 0.1639 0.01791 0.00924 -0.0806 0.7855 0.6068
-1.000 0.1851 0.01792 0.00929 -0.0793 0.7780 0.6257
-0.750 0.2180 0.01774 0.00911 -0.0800 0.7741 0.6467
-0.500 0.2403 0.01775 0.00918 -0.0788 0.7673 0.6663
-0.250 0.2664 0.01768 0.00917 -0.0782 0.7612 0.6876
0.000 0.3001 0.01749 0.00900 -0.0790 0.7575 0.7106
0.250 0.3187 0.01760 0.00917 -0.0772 0.7494 0.7320
0.500 0.3482 0.01749 0.00911 -0.0772 0.7442 0.7551
0.750 0.3837 0.01728 0.00892 -0.0783 0.7407 0.7804
1.000 0.4001 0.01744 0.00917 -0.0761 0.7316 0.8062
1.250 0.4347 0.01728 0.00906 -0.0771 0.7270 0.8347
1.500 0.4659 0.01726 0.00912 -0.0775 0.7196 0.8668
1.750 0.5108 0.01709 0.00900 -0.0806 0.7120 0.9000
2.000 0.5592 0.01702 0.00894 -0.0847 0.7028 0.9341
2.250 0.6117 0.01687 0.00878 -0.0896 0.6951 0.9673
2.500 0.6531 0.01701 0.00891 -0.0927 0.6869 1.0000
2.750 0.6763 0.01703 0.00888 -0.0920 0.6797 1.0000
3.000 0.6942 0.01718 0.00900 -0.0903 0.6716 1.0000
3.250 0.7186 0.01725 0.00903 -0.0897 0.6642 1.0000
3.500 0.7389 0.01742 0.00919 -0.0883 0.6562 1.0000
3.750 0.7633 0.01753 0.00929 -0.0877 0.6486 1.0000
4.000 0.7849 0.01771 0.00947 -0.0866 0.6407 1.0000
4.250 0.8092 0.01784 0.00961 -0.0859 0.6327 1.0000
4.500 0.8304 0.01805 0.00983 -0.0847 0.6242 1.0000
4.750 0.8556 0.01818 0.00997 -0.0842 0.6162 1.0000
5.000 0.8757 0.01844 0.01028 -0.0829 0.6075 1.0000
5.250 0.9018 0.01858 0.01044 -0.0825 0.5996 1.0000
5.500 0.9201 0.01888 0.01079 -0.0808 0.5901 1.0000
5.750 0.9488 0.01899 0.01092 -0.0809 0.5820 1.0000
6.000 0.9639 0.01934 0.01136 -0.0787 0.5716 1.0000
6.250 0.9872 0.01956 0.01162 -0.0778 0.5624 1.0000
6.500 1.0086 0.01977 0.01187 -0.0766 0.5514 1.0000
6.750 1.0238 0.02005 0.01220 -0.0743 0.5378 1.0000
7.000 1.0385 0.02025 0.01241 -0.0718 0.5214 1.0000
7.250 1.0507 0.02045 0.01258 -0.0688 0.5033 1.0000
7.500 1.0573 0.02078 0.01289 -0.0649 0.4828 1.0000
7.750 1.0627 0.02119 0.01327 -0.0610 0.4601 1.0000
8.000 1.0683 0.02168 0.01369 -0.0573 0.4349 1.0000
8.250 1.0743 0.02227 0.01419 -0.0539 0.4090 1.0000
8.500 1.0805 0.02298 0.01482 -0.0507 0.3835 1.0000
8.750 1.0879 0.02375 0.01550 -0.0478 0.3612 1.0000
9.000 1.0943 0.02463 0.01633 -0.0450 0.3380 1.0000
9.250 1.0989 0.02566 0.01729 -0.0421 0.3143 1.0000
9.500 1.1022 0.02684 0.01840 -0.0392 0.2862 1.0000
9.750 1.1026 0.02825 0.01970 -0.0362 0.2499 1.0000
10.000 1.0961 0.03017 0.02135 -0.0329 0.1964 1.0000
10.250 1.0861 0.03256 0.02339 -0.0296 0.1574 1.0000
10.500 1.0821 0.03475 0.02542 -0.0271 0.1294 1.0000
10.750 1.0797 0.03693 0.02749 -0.0249 0.1070 1.0000
11.000 1.0780 0.03915 0.02963 -0.0230 0.0921 1.0000
11.250 1.0761 0.04147 0.03192 -0.0213 0.0833 1.0000
11.500 1.0771 0.04362 0.03414 -0.0199 0.0765 1.0000
11.750 1.0760 0.04603 0.03656 -0.0186 0.0720 1.0000
12.000 1.0771 0.04833 0.03892 -0.0174 0.0681 1.0000
12.250 1.0795 0.05056 0.04126 -0.0164 0.0650 1.0000
12.500 1.0813 0.05291 0.04368 -0.0156 0.0624 1.0000
12.750 1.0822 0.05538 0.04618 -0.0148 0.0603 1.0000
13.000 1.0869 0.05751 0.04841 -0.0140 0.0580 1.0000
13.250 1.0929 0.05956 0.05056 -0.0134 0.0556 1.0000
13.500 1.0987 0.06164 0.05271 -0.0128 0.0535 1.0000
13.750 1.1047 0.06373 0.05483 -0.0123 0.0518 1.0000
14.000 1.1116 0.06569 0.05677 -0.0117 0.0501 1.0000
14.250 1.1213 0.06749 0.05872 -0.0111 0.0483 1.0000
14.500 1.1299 0.06942 0.06077 -0.0106 0.0465 1.0000
14.750 1.1380 0.07143 0.06288 -0.0103 0.0448 1.0000
15.000 1.1461 0.07344 0.06492 -0.0099 0.0434 1.0000
15.250 1.1570 0.07513 0.06655 -0.0094 0.0418 1.0000
15.500 1.1625 0.07765 0.06931 -0.0092 0.0405 1.0000
15.750 1.1684 0.08015 0.07201 -0.0091 0.0392 1.0000
16.000 1.1730 0.08282 0.07484 -0.0091 0.0380 1.0000
16.250 1.1763 0.08561 0.07775 -0.0093 0.0369 1.0000
16.500 1.1804 0.08829 0.08051 -0.0096 0.0358 1.0000
16.750 1.1892 0.09043 0.08262 -0.0095 0.0347 1.0000
17.000 1.1847 0.09447 0.08693 -0.0103 0.0340 1.0000
17.250 1.1785 0.09888 0.09162 -0.0115 0.0334 1.0000
17.500 1.1704 0.10365 0.09666 -0.0130 0.0327 1.0000
17.750 1.1612 0.10869 0.10193 -0.0148 0.0322 1.0000
18.000 1.1502 0.11412 0.10759 -0.0171 0.0317 1.0000
18.250 1.1377 0.11998 0.11367 -0.0198 0.0312 1.0000
18.500 1.1231 0.12642 0.12032 -0.0232 0.0308 1.0000
18.750 1.1063 0.13358 0.12769 -0.0272 0.0305 1.0000
19.000 1.0824 0.14267 0.13701 -0.0327 0.0304 1.0000
19.250 1.0178 0.16304 0.15775 -0.0457 0.0315 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 493 AIRFOIL (goe493-il)