GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Reynolds number: 100,000 Max Cl/Cd: 48.7 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe314-il-100000.txt Download as CSV file: xf-goe314-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 314 (HANSA-BRANDENBURG) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3048 0.09454 0.08966 -0.0231 1.0000 0.0656
-7.500 -0.3080 0.09266 0.08787 -0.0231 1.0000 0.0669
-7.250 -0.3141 0.09123 0.08654 -0.0240 1.0000 0.0682
-7.000 -0.3183 0.09057 0.08595 -0.0285 1.0000 0.0692
-6.750 -0.3184 0.09010 0.08545 -0.0334 1.0000 0.0696
-6.500 -0.3163 0.08530 0.08076 -0.0310 1.0000 0.0702
-6.250 -0.3137 0.08113 0.07670 -0.0261 1.0000 0.0714
-6.000 -0.3133 0.07858 0.07421 -0.0234 1.0000 0.0727
-5.750 -0.3146 0.07653 0.07222 -0.0216 1.0000 0.0744
-5.500 -0.3161 0.07463 0.07035 -0.0204 1.0000 0.0762
-5.250 -0.3158 0.07270 0.06844 -0.0200 1.0000 0.0782
-5.000 -0.3095 0.07106 0.06674 -0.0219 1.0000 0.0811
-4.750 -0.2916 0.07054 0.06589 -0.0279 1.0000 0.0832
-4.500 -0.2917 0.06636 0.06187 -0.0251 1.0000 0.0839
-4.250 -0.2663 0.06211 0.05768 -0.0272 0.9944 0.0864
-4.000 -0.2237 0.05842 0.05388 -0.0337 0.9856 0.0920
-3.750 -0.1739 0.05462 0.04980 -0.0423 0.9757 0.0989
-3.500 -0.1358 0.05120 0.04634 -0.0466 0.9666 0.1051
-3.250 -0.0855 0.04776 0.04261 -0.0538 0.9575 0.1135
-3.000 -0.0383 0.04591 0.04038 -0.0592 0.9455 0.1260
-2.750 -0.0064 0.04190 0.03652 -0.0617 0.9351 0.1318
-2.500 0.0428 0.03899 0.03344 -0.0670 0.9274 0.1483
-2.250 0.0837 0.03680 0.03103 -0.0706 0.9148 0.1740
-2.000 0.1242 0.03447 0.02860 -0.0738 0.9033 0.2045
-1.750 0.1625 0.03153 0.02570 -0.0764 0.8926 0.2392
-1.250 0.2288 0.02693 0.02109 -0.0785 0.8644 0.3473
-1.000 0.2564 0.02486 0.01904 -0.0779 0.8452 0.3847
-0.750 0.2860 0.02323 0.01730 -0.0775 0.8241 0.4137
-0.500 0.3235 0.02210 0.01581 -0.0785 0.8028 0.4068
-0.250 0.3926 0.02277 0.01482 -0.0811 0.7806 0.1698
0.000 0.4236 0.02168 0.01329 -0.0797 0.7568 0.1367
0.250 0.4534 0.02097 0.01215 -0.0785 0.7349 0.1235
0.500 0.4791 0.02029 0.01127 -0.0773 0.7106 0.1232
0.750 0.5062 0.01960 0.01037 -0.0763 0.6897 0.1220
1.000 0.5327 0.01903 0.00963 -0.0752 0.6692 0.1203
1.250 0.5588 0.01862 0.00908 -0.0742 0.6494 0.1202
1.500 0.5849 0.01831 0.00863 -0.0733 0.6314 0.1228
1.750 0.6101 0.01791 0.00821 -0.0723 0.6145 0.1293
2.000 0.6362 0.01772 0.00792 -0.0714 0.5982 0.1355
2.250 0.6617 0.01760 0.00766 -0.0705 0.5822 0.1434
2.500 0.6870 0.01755 0.00755 -0.0697 0.5669 0.1638
2.750 0.7377 0.01584 0.00739 -0.0739 0.5494 1.0000
3.000 0.7619 0.01620 0.00745 -0.0728 0.5357 1.0000
3.250 0.7859 0.01659 0.00766 -0.0719 0.5227 1.0000
3.500 0.8104 0.01700 0.00788 -0.0710 0.5107 1.0000
3.750 0.8350 0.01741 0.00814 -0.0702 0.4989 1.0000
4.000 0.8582 0.01783 0.00854 -0.0693 0.4866 1.0000
4.250 0.8820 0.01828 0.00893 -0.0684 0.4749 1.0000
4.500 0.9065 0.01873 0.00927 -0.0676 0.4639 1.0000
4.750 0.9301 0.01917 0.00966 -0.0667 0.4523 1.0000
5.000 0.9529 0.01966 0.01018 -0.0658 0.4406 1.0000
5.250 0.9768 0.02018 0.01065 -0.0650 0.4301 1.0000
5.500 1.0011 0.02064 0.01102 -0.0642 0.4193 1.0000
5.750 1.0229 0.02112 0.01158 -0.0631 0.4072 1.0000
6.000 1.0455 0.02161 0.01209 -0.0622 0.3958 1.0000
6.250 1.0695 0.02202 0.01241 -0.0614 0.3852 1.0000
6.500 1.0914 0.02241 0.01284 -0.0603 0.3735 1.0000
6.750 1.1128 0.02292 0.01345 -0.0592 0.3628 1.0000
7.000 1.1375 0.02340 0.01384 -0.0586 0.3546 1.0000
7.250 1.1581 0.02398 0.01460 -0.0574 0.3452 1.0000
7.500 1.1820 0.02453 0.01513 -0.0568 0.3379 1.0000
7.750 1.2027 0.02510 0.01589 -0.0556 0.3295 1.0000
8.000 1.2268 0.02565 0.01642 -0.0550 0.3230 1.0000
8.250 1.2464 0.02629 0.01729 -0.0538 0.3153 1.0000
8.500 1.2720 0.02671 0.01762 -0.0534 0.3092 1.0000
8.750 1.2893 0.02748 0.01874 -0.0519 0.3021 1.0000
9.000 1.3124 0.02795 0.01926 -0.0512 0.2962 1.0000
9.250 1.3319 0.02861 0.02012 -0.0500 0.2897 1.0000
9.500 1.3521 0.02900 0.02065 -0.0488 0.2823 1.0000
9.750 1.3698 0.02928 0.02110 -0.0473 0.2732 1.0000
10.000 1.3893 0.02917 0.02099 -0.0458 0.2627 1.0000
10.250 1.4026 0.02911 0.02105 -0.0435 0.2499 1.0000
10.500 1.4113 0.02904 0.02108 -0.0407 0.2344 1.0000
10.750 1.4172 0.02930 0.02152 -0.0375 0.2184 1.0000
11.000 1.4207 0.02982 0.02227 -0.0342 0.1998 1.0000
11.250 1.4183 0.03063 0.02312 -0.0302 0.1787 1.0000
11.500 1.4115 0.03199 0.02449 -0.0261 0.1529 1.0000
11.750 1.4011 0.03404 0.02645 -0.0225 0.1249 1.0000
12.000 1.3880 0.03671 0.02899 -0.0196 0.1060 1.0000
12.250 1.3724 0.03999 0.03217 -0.0176 0.0957 1.0000
12.500 1.3565 0.04373 0.03588 -0.0164 0.0892 1.0000
12.750 1.3408 0.04784 0.04002 -0.0158 0.0839 1.0000
13.000 1.3268 0.05210 0.04433 -0.0158 0.0796 1.0000
13.250 1.3127 0.05646 0.04861 -0.0157 0.0754 1.0000
13.500 1.3066 0.06015 0.05241 -0.0157 0.0712 1.0000
13.750 1.3085 0.06261 0.05469 -0.0142 0.0664 1.0000
14.000 1.3202 0.06444 0.05658 -0.0122 0.0623 1.0000
14.250 1.3261 0.06709 0.05933 -0.0114 0.0589 1.0000
14.500 1.3639 0.06805 0.06006 -0.0080 0.0537 1.0000
14.750 1.3574 0.07183 0.06413 -0.0084 0.0528 1.0000
15.000 1.3537 0.07571 0.06827 -0.0088 0.0520 1.0000
15.250 1.3468 0.08005 0.07287 -0.0097 0.0513 1.0000
15.500 1.3380 0.08475 0.07782 -0.0109 0.0509 1.0000
15.750 1.3258 0.08999 0.08331 -0.0127 0.0506 1.0000
16.000 1.3106 0.09581 0.08938 -0.0152 0.0505 1.0000
16.250 1.2919 0.10238 0.09620 -0.0185 0.0505 1.0000
16.500 1.2705 0.10972 0.10377 -0.0226 0.0508 1.0000
16.750 1.2462 0.11802 0.11230 -0.0277 0.0511 1.0000
17.000 1.2197 0.12731 0.12180 -0.0336 0.0518 1.0000
17.250 1.1908 0.13776 0.13243 -0.0405 0.0525 1.0000
17.500 1.1617 0.14917 0.14397 -0.0479 0.0534 1.0000
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Polar data table (+)
Polar graphs
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