GOE 796 AIRFOIL (goe796-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 796 AIRFOIL (goe796-il) Reynolds number: 100,000 Max Cl/Cd: 55.62 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe796-il-100000-n5.txt Download as CSV file: xf-goe796-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 796 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.4044 0.09233 0.08701 -0.0490 1.0000 0.0403
-9.500 -0.4114 0.08866 0.08342 -0.0494 1.0000 0.0401
-9.250 -0.4221 0.08503 0.07987 -0.0495 1.0000 0.0399
-9.000 -0.4381 0.08148 0.07641 -0.0491 1.0000 0.0398
-8.750 -0.4612 0.07825 0.07331 -0.0478 1.0000 0.0395
-8.500 -0.4907 0.07508 0.07026 -0.0461 1.0000 0.0393
-8.250 -0.5057 0.06594 0.06106 -0.0539 0.9945 0.0389
-8.000 -0.5247 0.04789 0.04227 -0.0678 0.9823 0.0383
-7.750 -0.5179 0.03985 0.03341 -0.0717 0.9734 0.0386
-7.500 -0.4990 0.03516 0.02803 -0.0736 0.9667 0.0392
-7.250 -0.4739 0.03185 0.02412 -0.0751 0.9608 0.0401
-7.000 -0.4427 0.02955 0.02143 -0.0770 0.9569 0.0411
-6.750 -0.4167 0.02832 0.02007 -0.0775 0.9494 0.0424
-6.500 -0.3837 0.02697 0.01853 -0.0792 0.9452 0.0443
-6.250 -0.3531 0.02557 0.01686 -0.0802 0.9399 0.0472
-6.000 -0.3246 0.02432 0.01538 -0.0807 0.9331 0.0507
-5.750 -0.2909 0.02345 0.01445 -0.0823 0.9289 0.0562
-5.500 -0.2636 0.02280 0.01371 -0.0825 0.9214 0.0630
-5.250 -0.2317 0.02228 0.01306 -0.0834 0.9157 0.0715
-5.000 -0.1978 0.02206 0.01277 -0.0848 0.9111 0.0801
-4.750 -0.1716 0.02185 0.01250 -0.0846 0.9025 0.0876
-4.500 -0.1382 0.02148 0.01192 -0.0856 0.8979 0.0968
-4.250 -0.1120 0.02127 0.01172 -0.0855 0.8898 0.1051
-4.000 -0.0811 0.02078 0.01111 -0.0861 0.8842 0.1134
-3.750 -0.0524 0.02031 0.01063 -0.0864 0.8779 0.1204
-3.250 0.0072 0.01932 0.00955 -0.0870 0.8665 0.1357
-3.000 0.0320 0.01903 0.00921 -0.0864 0.8579 0.1446
-2.750 0.0621 0.01863 0.00882 -0.0868 0.8528 0.1545
-2.500 0.0883 0.01834 0.00855 -0.0865 0.8455 0.1637
-2.250 0.1170 0.01805 0.00823 -0.0866 0.8394 0.1753
-2.000 0.1455 0.01776 0.00799 -0.0867 0.8338 0.1912
-1.750 0.1716 0.01753 0.00786 -0.0864 0.8265 0.2135
-1.500 0.2015 0.01715 0.00759 -0.0867 0.8217 0.2447
-1.250 0.2265 0.01691 0.00751 -0.0862 0.8140 0.2868
-1.000 0.2548 0.01641 0.00732 -0.0863 0.8082 0.3689
-0.750 0.2785 0.01575 0.00727 -0.0854 0.8007 0.5294
-0.500 0.3023 0.01498 0.00728 -0.0834 0.7934 0.7654
-0.250 0.3662 0.01469 0.00713 -0.0897 0.7856 0.9630
0.000 0.4141 0.01456 0.00682 -0.0935 0.7764 1.0000
0.250 0.4375 0.01459 0.00672 -0.0925 0.7654 1.0000
0.500 0.4634 0.01460 0.00658 -0.0918 0.7567 1.0000
0.750 0.4879 0.01468 0.00656 -0.0911 0.7480 1.0000
1.000 0.5135 0.01476 0.00654 -0.0905 0.7407 1.0000
1.250 0.5383 0.01486 0.00657 -0.0898 0.7324 1.0000
1.500 0.5638 0.01496 0.00658 -0.0892 0.7246 1.0000
1.750 0.5889 0.01507 0.00664 -0.0886 0.7162 1.0000
2.000 0.6141 0.01520 0.00671 -0.0880 0.7081 1.0000
2.250 0.6396 0.01532 0.00678 -0.0874 0.6997 1.0000
2.500 0.6642 0.01547 0.00691 -0.0867 0.6906 1.0000
2.750 0.6906 0.01557 0.00694 -0.0862 0.6820 1.0000
3.000 0.7142 0.01575 0.00712 -0.0853 0.6715 1.0000
3.250 0.7396 0.01588 0.00723 -0.0847 0.6619 1.0000
3.500 0.7647 0.01600 0.00734 -0.0840 0.6513 1.0000
3.750 0.7883 0.01616 0.00751 -0.0831 0.6387 1.0000
4.000 0.8122 0.01630 0.00765 -0.0822 0.6251 1.0000
4.250 0.8360 0.01643 0.00777 -0.0813 0.6102 1.0000
4.500 0.8596 0.01657 0.00790 -0.0803 0.5945 1.0000
4.750 0.8830 0.01673 0.00807 -0.0793 0.5785 1.0000
5.000 0.9063 0.01691 0.00824 -0.0783 0.5619 1.0000
5.250 0.9293 0.01711 0.00841 -0.0773 0.5441 1.0000
5.500 0.9515 0.01734 0.00861 -0.0761 0.5244 1.0000
5.750 0.9733 0.01761 0.00886 -0.0749 0.5035 1.0000
6.000 0.9948 0.01792 0.00910 -0.0737 0.4828 1.0000
6.250 1.0162 0.01827 0.00940 -0.0725 0.4643 1.0000
6.500 1.0375 0.01866 0.00976 -0.0713 0.4468 1.0000
6.750 1.0582 0.01908 0.01017 -0.0701 0.4297 1.0000
7.000 1.0785 0.01955 0.01060 -0.0688 0.4133 1.0000
7.250 1.0981 0.02004 0.01107 -0.0674 0.3968 1.0000
7.500 1.1165 0.02058 0.01156 -0.0659 0.3791 1.0000
7.750 1.1336 0.02117 0.01211 -0.0642 0.3608 1.0000
8.000 1.1502 0.02179 0.01269 -0.0624 0.3434 1.0000
8.250 1.1665 0.02241 0.01330 -0.0607 0.3270 1.0000
8.500 1.1820 0.02306 0.01396 -0.0588 0.3108 1.0000
8.750 1.1967 0.02372 0.01465 -0.0569 0.2943 1.0000
9.000 1.2099 0.02438 0.01539 -0.0547 0.2771 1.0000
9.250 1.2213 0.02509 0.01614 -0.0523 0.2592 1.0000
9.500 1.2319 0.02588 0.01696 -0.0499 0.2412 1.0000
9.750 1.2412 0.02679 0.01786 -0.0475 0.2237 1.0000
10.000 1.2494 0.02783 0.01886 -0.0451 0.2079 1.0000
10.250 1.2570 0.02898 0.01999 -0.0428 0.1942 1.0000
10.500 1.2646 0.03021 0.02121 -0.0406 0.1825 1.0000
10.750 1.2717 0.03154 0.02255 -0.0385 0.1717 1.0000
11.000 1.2770 0.03302 0.02402 -0.0364 0.1616 1.0000
11.250 1.2823 0.03457 0.02558 -0.0345 0.1510 1.0000
11.500 1.2890 0.03606 0.02717 -0.0328 0.1399 1.0000
11.750 1.2944 0.03769 0.02888 -0.0312 0.1298 1.0000
12.000 1.2982 0.03949 0.03071 -0.0297 0.1208 1.0000
12.250 1.3051 0.04113 0.03250 -0.0285 0.1116 1.0000
12.500 1.3088 0.04308 0.03451 -0.0273 0.1040 1.0000
12.750 1.3110 0.04522 0.03670 -0.0262 0.0962 1.0000
13.000 1.3132 0.04744 0.03902 -0.0252 0.0888 1.0000
13.250 1.3111 0.05014 0.04173 -0.0244 0.0826 1.0000
13.500 1.3124 0.05262 0.04434 -0.0237 0.0760 1.0000
13.750 1.3083 0.05571 0.04749 -0.0231 0.0711 1.0000
14.000 1.3074 0.05857 0.05051 -0.0226 0.0656 1.0000
14.250 1.3023 0.06201 0.05402 -0.0224 0.0610 1.0000
14.500 1.2980 0.06550 0.05762 -0.0224 0.0565 1.0000
14.750 1.2929 0.06921 0.06146 -0.0226 0.0524 1.0000
15.000 1.2840 0.07351 0.06582 -0.0232 0.0496 1.0000
15.250 1.2794 0.07740 0.06987 -0.0236 0.0464 1.0000
15.500 1.2727 0.08171 0.07432 -0.0244 0.0438 1.0000
15.750 1.2639 0.08644 0.07915 -0.0256 0.0419 1.0000
16.000 1.2549 0.09128 0.08406 -0.0269 0.0403 1.0000
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