GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Reynolds number: 200,000 Max Cl/Cd: 73.3 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe275-il-200000-n5.txt Download as CSV file: xf-goe275-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3153 0.09597 0.09258 -0.0243 1.0000 0.0222
-7.750 -0.3306 0.09491 0.09161 -0.0229 1.0000 0.0223
-7.500 -0.3434 0.09361 0.09039 -0.0208 1.0000 0.0223
-7.250 -0.3246 0.08896 0.08575 -0.0288 0.9956 0.0224
-7.000 -0.3072 0.08485 0.08164 -0.0285 0.9928 0.0227
-6.750 -0.2841 0.08071 0.07749 -0.0330 0.9878 0.0232
-6.500 -0.2603 0.07655 0.07331 -0.0389 0.9814 0.0239
-6.250 -0.2327 0.07214 0.06885 -0.0460 0.9759 0.0247
-6.000 -0.2043 0.06761 0.06427 -0.0541 0.9675 0.0262
-5.750 -0.1559 0.06115 0.05753 -0.0694 0.9583 0.0270
-5.500 -0.1380 0.05718 0.05360 -0.0706 0.9536 0.0274
-5.250 -0.1179 0.05413 0.05054 -0.0721 0.9470 0.0280
-5.000 -0.0890 0.05064 0.04697 -0.0760 0.9410 0.0290
-4.750 -0.0360 0.04621 0.04204 -0.0848 0.9351 0.0328
-4.500 -0.0092 0.04174 0.03744 -0.0877 0.9278 0.0334
-4.250 0.0214 0.03861 0.03430 -0.0908 0.9231 0.0343
-4.000 0.0497 0.03609 0.03167 -0.0926 0.9137 0.0357
-3.750 0.1005 0.03454 0.02937 -0.0965 0.9073 0.0409
-3.500 0.1229 0.03023 0.02515 -0.0981 0.8973 0.0424
-3.250 0.1551 0.02811 0.02293 -0.1001 0.8899 0.0443
-3.000 0.1947 0.01055 0.00506 -0.0978 0.8567 0.0519
-2.500 0.2460 0.00816 0.00234 -0.0985 0.8305 0.0644
-2.000 0.3037 0.02096 0.01450 -0.1030 0.8299 0.0778
-1.500 0.3647 0.01758 0.01025 -0.1013 0.7964 0.0418
-1.250 0.3926 0.01703 0.00948 -0.1008 0.7730 0.0414
-1.000 0.4199 0.01605 0.00832 -0.1004 0.7433 0.0400
-0.750 0.4463 0.01534 0.00733 -0.0997 0.7061 0.0393
-0.500 0.4713 0.01488 0.00656 -0.0987 0.6661 0.0390
-0.250 0.4953 0.01455 0.00597 -0.0975 0.6310 0.0389
0.000 0.5192 0.01430 0.00549 -0.0965 0.6002 0.0389
0.250 0.5433 0.01415 0.00515 -0.0954 0.5725 0.0396
0.500 0.5672 0.01417 0.00498 -0.0944 0.5447 0.0407
0.750 0.5910 0.01404 0.00471 -0.0934 0.5179 0.0409
1.000 0.6145 0.01389 0.00445 -0.0925 0.4911 0.0409
1.250 0.6379 0.01381 0.00426 -0.0915 0.4663 0.0410
1.500 0.6614 0.01370 0.00409 -0.0906 0.4433 0.0412
1.750 0.6851 0.01363 0.00395 -0.0897 0.4248 0.0417
2.000 0.7093 0.01364 0.00387 -0.0890 0.4098 0.0424
2.250 0.7340 0.01368 0.00384 -0.0883 0.3979 0.0434
2.500 0.7587 0.01377 0.00387 -0.0877 0.3882 0.0460
2.750 0.7834 0.01391 0.00392 -0.0870 0.3779 0.0488
3.000 0.8082 0.01405 0.00400 -0.0863 0.3674 0.0501
3.250 0.8326 0.01424 0.00410 -0.0856 0.3573 0.0523
3.500 0.8574 0.01439 0.00423 -0.0850 0.3481 0.0583
3.750 0.8889 0.01298 0.00457 -0.0861 0.3395 1.0000
4.000 0.9135 0.01323 0.00474 -0.0855 0.3313 1.0000
4.250 0.9380 0.01349 0.00493 -0.0848 0.3242 1.0000
4.500 0.9628 0.01372 0.00513 -0.0842 0.3170 1.0000
4.750 0.9868 0.01401 0.00537 -0.0835 0.3109 1.0000
5.000 1.0119 0.01422 0.00561 -0.0829 0.3044 1.0000
5.250 1.0361 0.01448 0.00586 -0.0823 0.2978 1.0000
5.500 1.0605 0.01473 0.00612 -0.0816 0.2910 1.0000
5.750 1.0846 0.01499 0.00640 -0.0809 0.2826 1.0000
6.000 1.1086 0.01523 0.00667 -0.0803 0.2727 1.0000
6.250 1.1320 0.01551 0.00695 -0.0795 0.2613 1.0000
6.500 1.1553 0.01579 0.00726 -0.0787 0.2504 1.0000
6.750 1.1786 0.01608 0.00757 -0.0779 0.2378 1.0000
7.000 1.2011 0.01642 0.00790 -0.0771 0.2234 1.0000
7.250 1.2227 0.01681 0.00827 -0.0761 0.2069 1.0000
7.500 1.2429 0.01732 0.00872 -0.0749 0.1901 1.0000
7.750 1.2627 0.01787 0.00922 -0.0737 0.1778 1.0000
8.000 1.2821 0.01845 0.00979 -0.0725 0.1675 1.0000
8.250 1.3023 0.01896 0.01037 -0.0713 0.1587 1.0000
8.500 1.3207 0.01959 0.01100 -0.0699 0.1502 1.0000
8.750 1.3409 0.02007 0.01158 -0.0688 0.1402 1.0000
9.000 1.3597 0.02064 0.01220 -0.0674 0.1292 1.0000
9.250 1.3773 0.02126 0.01286 -0.0660 0.1164 1.0000
9.500 1.3930 0.02199 0.01355 -0.0643 0.1044 1.0000
9.750 1.4060 0.02282 0.01433 -0.0622 0.0959 1.0000
10.000 1.4166 0.02372 0.01521 -0.0598 0.0897 1.0000
10.250 1.4277 0.02458 0.01612 -0.0574 0.0851 1.0000
10.500 1.4390 0.02542 0.01708 -0.0552 0.0814 1.0000
10.750 1.4484 0.02639 0.01812 -0.0528 0.0784 1.0000
11.000 1.4544 0.02756 0.01935 -0.0502 0.0754 1.0000
11.250 1.4660 0.02842 0.02035 -0.0483 0.0730 1.0000
11.500 1.4782 0.02925 0.02135 -0.0466 0.0692 1.0000
11.750 1.4867 0.03034 0.02256 -0.0446 0.0653 1.0000
12.000 1.4909 0.03177 0.02406 -0.0424 0.0623 1.0000
12.250 1.5043 0.03260 0.02508 -0.0411 0.0580 1.0000
12.500 1.5123 0.03385 0.02641 -0.0396 0.0508 1.0000
12.750 1.5186 0.03531 0.02790 -0.0380 0.0398 1.0000
13.000 1.5144 0.03772 0.03023 -0.0362 0.0263 1.0000
13.250 1.5070 0.04058 0.03311 -0.0346 0.0218 1.0000
13.500 1.5008 0.04357 0.03620 -0.0335 0.0199 1.0000
13.750 1.4926 0.04700 0.03974 -0.0329 0.0185 1.0000
14.000 1.4844 0.05072 0.04362 -0.0328 0.0175 1.0000
14.250 1.4764 0.05469 0.04776 -0.0332 0.0168 1.0000
14.500 1.4671 0.05909 0.05234 -0.0341 0.0162 1.0000
14.750 1.4568 0.06387 0.05730 -0.0354 0.0158 1.0000
15.000 1.4440 0.06929 0.06288 -0.0373 0.0153 1.0000
15.250 1.4305 0.07504 0.06880 -0.0394 0.0150 1.0000
15.500 1.4159 0.08121 0.07514 -0.0420 0.0148 1.0000
15.750 1.4006 0.08769 0.08178 -0.0448 0.0145 1.0000
16.000 1.3848 0.09445 0.08869 -0.0478 0.0143 1.0000
16.250 1.3696 0.10123 0.09563 -0.0510 0.0142 1.0000
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Polar data table (+)
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