GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL (goe346-il) Reynolds number: 100,000 Max Cl/Cd: 61.33 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe346-il-100000.txt Download as CSV file: xf-goe346-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 346 (FRIEDRICHSHAFEN-STAAKEN) 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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4343 0.11636 0.11115 -0.0101 1.0000 0.0457
-9.000 -0.4341 0.11516 0.11002 -0.0137 1.0000 0.0461
-8.750 -0.4350 0.11387 0.10880 -0.0175 1.0000 0.0464
-8.500 -0.4313 0.11200 0.10698 -0.0231 1.0000 0.0465
-8.250 -0.4226 0.10505 0.10005 -0.0195 1.0000 0.0472
-8.000 -0.4095 0.09935 0.09433 -0.0163 1.0000 0.0485
-7.750 -0.4031 0.09600 0.09102 -0.0165 1.0000 0.0498
-7.500 -0.3971 0.09295 0.08800 -0.0177 1.0000 0.0515
-7.250 -0.3899 0.08993 0.08502 -0.0200 1.0000 0.0535
-7.000 -0.3812 0.08708 0.08219 -0.0235 1.0000 0.0556
-6.750 -0.3665 0.08542 0.08050 -0.0318 1.0000 0.0575
-6.500 -0.3477 0.08459 0.07949 -0.0400 1.0000 0.0582
-6.250 -0.3466 0.07823 0.07331 -0.0365 1.0000 0.0590
-6.000 -0.3431 0.07424 0.06940 -0.0333 1.0000 0.0603
-5.750 -0.3360 0.07120 0.06637 -0.0325 1.0000 0.0621
-5.500 -0.3265 0.06840 0.06357 -0.0329 1.0000 0.0644
-5.250 -0.3132 0.06577 0.06089 -0.0345 1.0000 0.0678
-5.000 -0.2839 0.06409 0.05887 -0.0412 1.0000 0.0719
-4.750 -0.2820 0.05988 0.05483 -0.0383 1.0000 0.0736
-4.500 -0.2725 0.05709 0.05205 -0.0373 1.0000 0.0763
-4.250 -0.2563 0.05462 0.04951 -0.0380 1.0000 0.0807
-4.000 -0.2260 0.05269 0.04719 -0.0418 1.0000 0.0865
-3.750 -0.2172 0.04926 0.04387 -0.0405 1.0000 0.0890
-3.500 -0.1882 0.04901 0.04322 -0.0424 1.0000 0.0995
-3.250 -0.1764 0.04470 0.03904 -0.0422 1.0000 0.1027
-3.000 -0.1505 0.04376 0.03776 -0.0434 1.0000 0.1150
-2.750 -0.1369 0.04033 0.03450 -0.0430 1.0000 0.1194
-2.500 -0.1132 0.03851 0.03246 -0.0439 1.0000 0.1316
-2.250 -0.0907 0.03670 0.03052 -0.0446 1.0000 0.1456
-2.000 -0.0690 0.03479 0.02856 -0.0451 1.0000 0.1617
-1.750 -0.0458 0.03322 0.02687 -0.0459 1.0000 0.1890
-1.500 -0.0245 0.03139 0.02508 -0.0464 1.0000 0.2241
-1.250 -0.0034 0.03016 0.02384 -0.0468 1.0000 0.2903
-1.000 0.0178 0.02769 0.02156 -0.0469 1.0000 0.3418
-0.750 0.0584 0.02597 0.01978 -0.0502 0.9961 0.3944
-0.500 0.1052 0.02413 0.01785 -0.0544 0.9909 0.4169
0.000 0.2280 0.02427 0.01634 -0.0639 0.9751 0.1972
0.250 0.2788 0.02359 0.01522 -0.0669 0.9683 0.1490
0.500 0.3278 0.02286 0.01420 -0.0698 0.9586 0.1237
0.750 0.3760 0.02210 0.01326 -0.0729 0.9466 0.1120
1.000 0.4246 0.02106 0.01225 -0.0763 0.9355 0.1070
1.250 0.4790 0.02007 0.01130 -0.0807 0.9274 0.1057
1.500 0.5233 0.01926 0.01059 -0.0831 0.9145 0.1118
1.750 0.5653 0.01849 0.00985 -0.0846 0.9007 0.1142
2.000 0.6034 0.01779 0.00918 -0.0855 0.8863 0.1205
2.250 0.6375 0.01729 0.00871 -0.0856 0.8715 0.1333
2.500 0.6677 0.01513 0.00841 -0.0849 0.8570 1.0000
2.750 0.6967 0.01496 0.00804 -0.0837 0.8405 1.0000
3.000 0.7245 0.01475 0.00773 -0.0824 0.8231 1.0000
3.250 0.7488 0.01464 0.00759 -0.0806 0.8010 1.0000
3.500 0.7748 0.01442 0.00735 -0.0789 0.7795 1.0000
3.750 0.7992 0.01432 0.00724 -0.0772 0.7532 1.0000
4.000 0.8238 0.01426 0.00714 -0.0754 0.7240 1.0000
4.250 0.8478 0.01423 0.00703 -0.0735 0.6877 1.0000
4.500 0.8701 0.01430 0.00701 -0.0714 0.6376 1.0000
4.750 0.8918 0.01454 0.00700 -0.0693 0.5769 1.0000
5.000 0.9124 0.01510 0.00717 -0.0673 0.5112 1.0000
5.250 0.9326 0.01582 0.00755 -0.0656 0.4458 1.0000
5.500 0.9530 0.01659 0.00801 -0.0642 0.3929 1.0000
5.750 0.9747 0.01735 0.00858 -0.0631 0.3541 1.0000
6.000 0.9964 0.01811 0.00920 -0.0621 0.3220 1.0000
6.250 1.0180 0.01882 0.00983 -0.0611 0.2909 1.0000
6.500 1.0392 0.01944 0.01045 -0.0601 0.2534 1.0000
6.750 1.0578 0.02034 0.01121 -0.0588 0.1912 1.0000
7.000 1.0717 0.02234 0.01258 -0.0567 0.1144 1.0000
7.250 1.0891 0.02385 0.01391 -0.0551 0.0944 1.0000
7.500 1.1072 0.02544 0.01548 -0.0535 0.0854 1.0000
7.750 1.1249 0.02731 0.01722 -0.0520 0.0784 1.0000
8.000 1.1463 0.02878 0.01887 -0.0508 0.0722 1.0000
8.250 1.1682 0.03081 0.02085 -0.0498 0.0683 1.0000
8.500 1.1917 0.03332 0.02349 -0.0490 0.0652 1.0000
8.750 1.2131 0.03525 0.02573 -0.0479 0.0615 1.0000
9.000 1.2344 0.03777 0.02850 -0.0468 0.0594 1.0000
9.250 1.2539 0.04072 0.03178 -0.0456 0.0582 1.0000
9.500 1.2706 0.04393 0.03525 -0.0443 0.0568 1.0000
9.750 1.2824 0.04900 0.04059 -0.0431 0.0552 1.0000
10.000 1.2871 0.05211 0.04425 -0.0405 0.0546 1.0000
10.250 1.2902 0.05656 0.04913 -0.0383 0.0548 1.0000
10.500 1.2922 0.06145 0.05439 -0.0363 0.0553 1.0000
10.750 1.2848 0.06419 0.05770 -0.0329 0.0565 1.0000
11.000 1.2429 0.06926 0.06349 -0.0281 0.0585 1.0000
11.250 1.2088 0.07433 0.06889 -0.0257 0.0597 1.0000
11.500 1.1767 0.08015 0.07496 -0.0259 0.0607 1.0000
11.750 1.1442 0.08721 0.08221 -0.0287 0.0616 1.0000
12.000 1.1106 0.09615 0.09129 -0.0342 0.0626 1.0000
12.250 1.0802 0.10681 0.10202 -0.0414 0.0641 1.0000
12.500 1.0661 0.11505 0.11023 -0.0453 0.0656 1.0000
12.750 1.0378 0.13291 0.12809 -0.0536 0.0790 1.0000
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Polar data table (+)
Polar graphs
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