GOE 210 (DAIMLER) AIRFOIL (goe210-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 210 (DAIMLER) AIRFOIL (goe210-il) Reynolds number: 100,000 Max Cl/Cd: 62.04 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe210-il-100000.txt Download as CSV file: xf-goe210-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 210 (DAIMLER) 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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3636 0.09956 0.09470 -0.0206 1.0000 0.0536
-7.750 -0.3639 0.09772 0.09294 -0.0227 1.0000 0.0549
-7.500 -0.3638 0.09630 0.09162 -0.0275 1.0000 0.0557
-7.250 -0.3578 0.09449 0.08985 -0.0344 1.0000 0.0562
-7.000 -0.3501 0.09151 0.08691 -0.0388 1.0000 0.0565
-6.750 -0.3485 0.08518 0.08067 -0.0285 1.0000 0.0586
-6.500 -0.3429 0.08222 0.07776 -0.0272 1.0000 0.0612
-6.250 -0.3372 0.07950 0.07509 -0.0283 1.0000 0.0643
-6.000 -0.3276 0.07715 0.07275 -0.0332 1.0000 0.0681
-5.750 -0.3063 0.07652 0.07185 -0.0443 1.0000 0.0697
-5.500 -0.3124 0.07069 0.06631 -0.0377 1.0000 0.0711
-5.250 -0.3114 0.06791 0.06359 -0.0345 1.0000 0.0730
-5.000 -0.3071 0.06551 0.06123 -0.0336 1.0000 0.0758
-4.750 -0.2968 0.06309 0.05875 -0.0351 1.0000 0.0803
-4.500 -0.2736 0.06017 0.05557 -0.0413 1.0000 0.0846
-4.250 -0.2710 0.05708 0.05260 -0.0386 1.0000 0.0868
-4.000 -0.2590 0.05462 0.05012 -0.0385 1.0000 0.0916
-3.750 -0.2321 0.05155 0.04678 -0.0429 1.0000 0.0994
-3.500 -0.2200 0.04896 0.04423 -0.0422 1.0000 0.1048
-3.250 -0.1970 0.04621 0.04131 -0.0444 1.0000 0.1161
-3.000 -0.1625 0.04320 0.03814 -0.0482 0.9970 0.1328
-2.750 -0.1178 0.04009 0.03474 -0.0540 0.9926 0.1573
-2.500 -0.0793 0.03730 0.03181 -0.0580 0.9876 0.1866
-2.250 -0.0427 0.03470 0.02922 -0.0613 0.9836 0.2326
-2.000 -0.0147 0.03254 0.02712 -0.0626 0.9779 0.3031
-1.750 0.0190 0.03026 0.02493 -0.0640 0.9731 0.3650
-1.500 0.1192 0.02667 0.01905 -0.0741 0.9707 0.1214
-1.250 0.1617 0.02479 0.01662 -0.0760 0.9653 0.1043
-1.000 0.2053 0.02380 0.01504 -0.0781 0.9594 0.0972
-0.750 0.2507 0.02235 0.01354 -0.0816 0.9554 0.1025
-0.500 0.2855 0.02157 0.01265 -0.0829 0.9470 0.1036
-0.250 0.3322 0.02071 0.01175 -0.0862 0.9417 0.1075
0.000 0.3673 0.02004 0.01113 -0.0875 0.9317 0.1150
0.250 0.4099 0.01931 0.01049 -0.0900 0.9223 0.1343
0.500 0.4587 0.01635 0.00952 -0.0928 0.9152 1.0000
0.750 0.4991 0.01614 0.00903 -0.0943 0.9024 1.0000
1.000 0.5378 0.01583 0.00855 -0.0954 0.8888 1.0000
1.250 0.5741 0.01544 0.00806 -0.0957 0.8744 1.0000
1.500 0.6066 0.01516 0.00769 -0.0954 0.8603 1.0000
1.750 0.6363 0.01503 0.00750 -0.0949 0.8470 1.0000
2.000 0.6648 0.01496 0.00739 -0.0942 0.8338 1.0000
2.250 0.6925 0.01490 0.00729 -0.0933 0.8197 1.0000
2.500 0.7195 0.01486 0.00724 -0.0922 0.8045 1.0000
2.750 0.7458 0.01484 0.00719 -0.0910 0.7885 1.0000
3.000 0.7719 0.01483 0.00716 -0.0897 0.7719 1.0000
3.250 0.7968 0.01487 0.00719 -0.0883 0.7533 1.0000
3.500 0.8212 0.01489 0.00725 -0.0869 0.7321 1.0000
3.750 0.8457 0.01486 0.00721 -0.0853 0.7090 1.0000
4.000 0.8695 0.01481 0.00716 -0.0836 0.6808 1.0000
4.250 0.8922 0.01473 0.00703 -0.0817 0.6425 1.0000
4.500 0.9136 0.01473 0.00693 -0.0795 0.5872 1.0000
4.750 0.9331 0.01504 0.00686 -0.0771 0.5097 1.0000
5.000 0.9513 0.01586 0.00715 -0.0750 0.4342 1.0000
5.250 0.9711 0.01682 0.00772 -0.0736 0.3862 1.0000
5.500 0.9929 0.01772 0.00841 -0.0725 0.3561 1.0000
5.750 1.0158 0.01851 0.00909 -0.0717 0.3327 1.0000
6.000 1.0390 0.01928 0.00978 -0.0710 0.3146 1.0000
6.250 1.0628 0.02004 0.01050 -0.0703 0.2998 1.0000
6.500 1.0861 0.02076 0.01122 -0.0697 0.2848 1.0000
6.750 1.1096 0.02149 0.01203 -0.0690 0.2713 1.0000
7.000 1.1328 0.02223 0.01286 -0.0683 0.2577 1.0000
7.250 1.1553 0.02301 0.01370 -0.0675 0.2430 1.0000
7.500 1.1758 0.02379 0.01454 -0.0665 0.2244 1.0000
7.750 1.1943 0.02451 0.01535 -0.0652 0.2023 1.0000
8.000 1.2118 0.02531 0.01618 -0.0639 0.1804 1.0000
8.250 1.2296 0.02611 0.01705 -0.0626 0.1613 1.0000
8.500 1.2482 0.02701 0.01806 -0.0613 0.1464 1.0000
8.750 1.2663 0.02776 0.01898 -0.0600 0.1324 1.0000
9.000 1.2827 0.02818 0.01958 -0.0586 0.1137 1.0000
9.250 1.2962 0.02916 0.02055 -0.0569 0.0882 1.0000
9.500 1.2986 0.03193 0.02309 -0.0538 0.0682 1.0000
9.750 1.3054 0.03466 0.02586 -0.0511 0.0577 1.0000
10.000 1.3160 0.03730 0.02866 -0.0489 0.0512 1.0000
10.250 1.3262 0.03942 0.03087 -0.0469 0.0461 1.0000
10.500 1.3408 0.04289 0.03438 -0.0456 0.0431 1.0000
10.750 1.3521 0.04552 0.03740 -0.0436 0.0414 1.0000
11.000 1.3603 0.04858 0.04082 -0.0415 0.0401 1.0000
11.250 1.3627 0.05177 0.04440 -0.0389 0.0392 1.0000
11.500 1.3598 0.05505 0.04802 -0.0362 0.0386 1.0000
11.750 1.3525 0.05837 0.05165 -0.0336 0.0381 1.0000
12.000 1.3420 0.06185 0.05543 -0.0314 0.0376 1.0000
12.250 1.3292 0.06560 0.05945 -0.0298 0.0372 1.0000
12.500 1.3131 0.06988 0.06401 -0.0291 0.0370 1.0000
12.750 1.2916 0.07506 0.06948 -0.0294 0.0372 1.0000
13.000 1.2640 0.08157 0.07630 -0.0312 0.0379 1.0000
13.250 1.2345 0.08912 0.08413 -0.0347 0.0387 1.0000
13.500 1.2046 0.09773 0.09296 -0.0396 0.0397 1.0000
13.750 1.1751 0.10741 0.10278 -0.0459 0.0406 1.0000
14.000 1.1460 0.11829 0.11378 -0.0532 0.0415 1.0000
14.250 1.1189 0.12992 0.12546 -0.0608 0.0425 1.0000
14.500 1.0981 0.14068 0.13621 -0.0669 0.0433 1.0000
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Polar data table (+)
Polar graphs
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