GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Reynolds number: 50,000 Max Cl/Cd: 34.44 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe275-il-50000.txt Download as CSV file: xf-goe275-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 275 (DAIMLER VI) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3349 0.11089 0.10387 -0.0224 1.0000 0.1288
-8.500 -0.3448 0.11051 0.10362 -0.0234 1.0000 0.1322
-8.250 -0.3606 0.11077 0.10405 -0.0239 1.0000 0.1331
-8.000 -0.3315 0.10325 0.09646 -0.0216 1.0000 0.1411
-7.750 -0.3383 0.10195 0.09529 -0.0212 1.0000 0.1461
-7.500 -0.3553 0.10203 0.09555 -0.0222 1.0000 0.1483
-7.250 -0.3393 0.09674 0.09027 -0.0190 1.0000 0.1561
-7.000 -0.3480 0.09564 0.08932 -0.0198 1.0000 0.1625
-6.750 -0.3475 0.09259 0.08636 -0.0191 1.0000 0.1674
-6.500 -0.3457 0.09024 0.08409 -0.0181 1.0000 0.1767
-6.250 -0.3485 0.08783 0.08178 -0.0186 1.0000 0.1825
-6.000 -0.3467 0.08557 0.07958 -0.0178 1.0000 0.1933
-5.500 -0.3453 0.08091 0.07505 -0.0194 1.0000 0.2122
-5.250 -0.3414 0.07872 0.07288 -0.0195 1.0000 0.2268
-5.000 -0.3368 0.07505 0.06931 -0.0144 1.0000 0.2388
-4.750 -0.3321 0.07340 0.06765 -0.0179 1.0000 0.2589
-4.500 -0.3289 0.07005 0.06441 -0.0140 1.0000 0.2762
-4.250 -0.3257 0.06731 0.06176 -0.0098 1.0000 0.2981
-4.000 0.0713 0.04106 0.03457 -0.0277 1.0000 1.0000
-3.750 0.0779 0.03962 0.03322 -0.0273 1.0000 1.0000
-3.500 0.0840 0.03828 0.03198 -0.0268 1.0000 1.0000
-3.250 0.0892 0.03703 0.03083 -0.0262 1.0000 1.0000
-3.000 0.0934 0.03586 0.02978 -0.0254 1.0000 1.0000
-2.750 0.0524 0.03684 0.03100 -0.0140 1.0000 0.9840
-2.500 0.0040 0.03780 0.03221 -0.0017 1.0000 0.9616
-2.250 -0.0472 0.03869 0.03333 0.0104 1.0000 0.9417
-2.000 -0.0955 0.03907 0.03394 0.0210 1.0000 0.9205
-1.750 -0.1454 0.03922 0.03433 0.0313 1.0000 0.9012
-1.500 -0.1993 0.03928 0.03461 0.0420 1.0000 0.8851
-1.250 -0.2646 0.03927 0.03484 0.0545 1.0000 0.8702
-1.000 -0.0190 0.03619 0.02889 -0.0419 1.0000 0.3087
-0.750 0.0213 0.03541 0.02728 -0.0452 1.0000 0.2417
-0.500 0.0541 0.03434 0.02589 -0.0471 0.9970 0.2174
-0.250 0.1248 0.03338 0.02424 -0.0546 0.9789 0.1864
0.000 0.1916 0.03257 0.02285 -0.0611 0.9600 0.1686
0.250 0.2492 0.03186 0.02179 -0.0661 0.9379 0.1602
0.500 0.3136 0.03103 0.02068 -0.0719 0.9174 0.1600
0.750 0.3696 0.03026 0.01973 -0.0760 0.8933 0.1606
1.000 0.4320 0.02926 0.01864 -0.0808 0.8715 0.1624
1.250 0.4842 0.02834 0.01773 -0.0840 0.8464 0.1691
1.500 0.5466 0.02707 0.01660 -0.0885 0.8251 0.1971
1.750 0.5980 0.02453 0.01588 -0.0910 0.8011 1.0000
2.000 0.6482 0.02400 0.01490 -0.0925 0.7782 1.0000
2.250 0.6838 0.02394 0.01456 -0.0925 0.7525 1.0000
2.500 0.7248 0.02372 0.01407 -0.0931 0.7316 1.0000
2.750 0.7534 0.02404 0.01421 -0.0925 0.7087 1.0000
3.000 0.7853 0.02425 0.01422 -0.0922 0.6887 1.0000
3.250 0.8176 0.02444 0.01422 -0.0919 0.6699 1.0000
3.500 0.8421 0.02496 0.01462 -0.0907 0.6492 1.0000
3.750 0.8678 0.02543 0.01497 -0.0896 0.6296 1.0000
4.000 0.8938 0.02596 0.01541 -0.0887 0.6117 1.0000
4.250 0.9186 0.02667 0.01606 -0.0878 0.5958 1.0000
4.500 0.9423 0.02751 0.01688 -0.0869 0.5810 1.0000
4.750 0.9654 0.02838 0.01775 -0.0859 0.5664 1.0000
5.000 0.9883 0.02928 0.01869 -0.0849 0.5521 1.0000
5.250 1.0111 0.03024 0.01968 -0.0840 0.5383 1.0000
5.500 1.0344 0.03123 0.02069 -0.0830 0.5251 1.0000
5.750 1.0585 0.03217 0.02166 -0.0821 0.5117 1.0000
6.000 1.0810 0.03312 0.02267 -0.0810 0.4967 1.0000
6.250 1.1013 0.03411 0.02372 -0.0795 0.4806 1.0000
6.500 1.1212 0.03513 0.02482 -0.0780 0.4644 1.0000
6.750 1.1403 0.03616 0.02593 -0.0764 0.4478 1.0000
7.000 1.1588 0.03710 0.02697 -0.0746 0.4301 1.0000
7.250 1.1786 0.03787 0.02780 -0.0729 0.4122 1.0000
7.500 1.1988 0.03871 0.02870 -0.0713 0.3952 1.0000
7.750 1.2175 0.03986 0.02994 -0.0697 0.3796 1.0000
8.000 1.2351 0.04118 0.03142 -0.0680 0.3642 1.0000
8.250 1.2532 0.04236 0.03270 -0.0663 0.3476 1.0000
8.500 1.2743 0.04324 0.03359 -0.0647 0.3293 1.0000
8.750 1.2975 0.04405 0.03433 -0.0633 0.3107 1.0000
9.000 1.3081 0.04596 0.03647 -0.0610 0.2942 1.0000
9.250 1.3221 0.04780 0.03843 -0.0590 0.2794 1.0000
9.500 1.3241 0.05046 0.04141 -0.0563 0.2673 1.0000
9.750 1.3178 0.05391 0.04519 -0.0533 0.2583 1.0000
10.000 1.3363 0.05535 0.04668 -0.0519 0.2480 1.0000
10.250 1.3100 0.06044 0.05217 -0.0482 0.2435 1.0000
10.500 1.3449 0.06126 0.05300 -0.0480 0.2352 1.0000
10.750 1.3039 0.06760 0.05965 -0.0444 0.2342 1.0000
11.000 1.2508 0.07471 0.06689 -0.0413 0.2346 1.0000
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Polar data table (+)
Polar graphs
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