GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Reynolds number: 100,000 Max Cl/Cd: 56.22 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe276-il-100000-n5.txt Download as CSV file: xf-goe276-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 276 (DAIMLER VII) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3671 0.09368 0.08891 -0.0211 1.0000 0.0363
-7.250 -0.3639 0.09089 0.08619 -0.0217 1.0000 0.0379
-7.000 -0.3602 0.08805 0.08340 -0.0230 1.0000 0.0396
-6.750 -0.3553 0.08510 0.08050 -0.0250 1.0000 0.0415
-6.500 -0.3468 0.08216 0.07759 -0.0292 1.0000 0.0436
-6.250 -0.3299 0.07924 0.07462 -0.0370 1.0000 0.0448
-6.000 -0.3139 0.07596 0.07125 -0.0413 1.0000 0.0452
-5.750 -0.2987 0.07252 0.06769 -0.0441 1.0000 0.0453
-5.500 -0.2910 0.06768 0.06289 -0.0444 1.0000 0.0459
-5.250 -0.2932 0.06437 0.05974 -0.0402 1.0000 0.0475
-5.000 -0.2850 0.06187 0.05726 -0.0392 1.0000 0.0503
-4.750 -0.2672 0.05878 0.05408 -0.0412 1.0000 0.0540
-4.500 -0.2057 0.05349 0.04814 -0.0538 0.9959 0.0596
-4.250 -0.1834 0.04921 0.04399 -0.0555 0.9919 0.0623
-4.000 -0.1349 0.04561 0.03991 -0.0627 0.9873 0.0742
-3.750 -0.1054 0.04203 0.03636 -0.0653 0.9822 0.0777
-3.500 -0.0605 0.03882 0.03268 -0.0707 0.9775 0.0895
-3.000 0.0269 0.03148 0.02432 -0.0769 0.9671 0.0571
-2.750 0.0639 0.02884 0.02139 -0.0794 0.9603 0.0548
-2.500 0.1061 0.02683 0.01893 -0.0823 0.9544 0.0559
-2.250 0.1437 0.02513 0.01686 -0.0841 0.9460 0.0562
-2.000 0.1843 0.02341 0.01484 -0.0866 0.9407 0.0550
-1.750 0.2193 0.02210 0.01327 -0.0878 0.9329 0.0542
-1.500 0.2576 0.02088 0.01179 -0.0896 0.9265 0.0539
-1.250 0.2923 0.01988 0.01062 -0.0907 0.9172 0.0540
-1.000 0.3303 0.01896 0.00954 -0.0923 0.9093 0.0551
-0.750 0.3648 0.01840 0.00883 -0.0933 0.8981 0.0581
-0.500 0.3985 0.01774 0.00810 -0.0941 0.8857 0.0587
-0.250 0.4313 0.01707 0.00741 -0.0947 0.8715 0.0589
0.000 0.4628 0.01644 0.00681 -0.0950 0.8553 0.0593
0.250 0.4930 0.01591 0.00627 -0.0951 0.8365 0.0602
0.500 0.5208 0.01556 0.00587 -0.0947 0.8124 0.0615
0.750 0.5484 0.01531 0.00553 -0.0941 0.7825 0.0635
1.000 0.5758 0.01515 0.00521 -0.0934 0.7422 0.0665
1.250 0.6034 0.01506 0.00487 -0.0927 0.6874 0.0710
1.500 0.6305 0.01509 0.00458 -0.0919 0.6315 0.0823
1.750 0.6506 0.01323 0.00450 -0.0901 0.5900 1.0000
2.000 0.6765 0.01361 0.00450 -0.0894 0.5558 1.0000
2.250 0.7024 0.01398 0.00460 -0.0889 0.5297 1.0000
2.500 0.7286 0.01434 0.00474 -0.0885 0.5095 1.0000
2.750 0.7549 0.01470 0.00493 -0.0881 0.4932 1.0000
3.000 0.7812 0.01506 0.00517 -0.0878 0.4789 1.0000
3.250 0.8075 0.01544 0.00542 -0.0875 0.4652 1.0000
3.500 0.8336 0.01583 0.00570 -0.0872 0.4521 1.0000
3.750 0.8597 0.01622 0.00603 -0.0869 0.4396 1.0000
4.000 0.8859 0.01659 0.00637 -0.0866 0.4270 1.0000
4.250 0.9119 0.01696 0.00673 -0.0863 0.4143 1.0000
4.500 0.9376 0.01734 0.00712 -0.0859 0.4017 1.0000
4.750 0.9633 0.01771 0.00750 -0.0856 0.3892 1.0000
5.000 0.9888 0.01807 0.00789 -0.0852 0.3769 1.0000
5.250 1.0143 0.01843 0.00830 -0.0848 0.3654 1.0000
5.500 1.0399 0.01876 0.00877 -0.0845 0.3534 1.0000
5.750 1.0653 0.01912 0.00923 -0.0841 0.3417 1.0000
6.000 1.0904 0.01949 0.00970 -0.0836 0.3299 1.0000
6.250 1.1152 0.01987 0.01021 -0.0831 0.3178 1.0000
6.500 1.1396 0.02027 0.01071 -0.0826 0.3054 1.0000
6.750 1.1636 0.02071 0.01125 -0.0819 0.2928 1.0000
7.000 1.1870 0.02115 0.01179 -0.0812 0.2764 1.0000
7.250 1.2084 0.02163 0.01226 -0.0803 0.2511 1.0000
7.500 1.2297 0.02223 0.01291 -0.0794 0.2276 1.0000
7.750 1.2508 0.02290 0.01362 -0.0785 0.2070 1.0000
8.000 1.2706 0.02368 0.01437 -0.0775 0.1748 1.0000
8.250 1.2878 0.02480 0.01528 -0.0762 0.1335 1.0000
8.750 1.3083 0.02886 0.01871 -0.0721 0.0373 1.0000
9.000 1.3203 0.03054 0.02051 -0.0699 0.0306 1.0000
9.250 1.3309 0.03222 0.02233 -0.0676 0.0272 1.0000
9.500 1.3409 0.03381 0.02413 -0.0654 0.0244 1.0000
9.750 1.3469 0.03561 0.02612 -0.0627 0.0226 1.0000
10.000 1.3474 0.03765 0.02835 -0.0595 0.0216 1.0000
10.250 1.3438 0.03967 0.03054 -0.0557 0.0210 1.0000
10.500 1.3420 0.04173 0.03281 -0.0525 0.0206 1.0000
10.750 1.3392 0.04403 0.03532 -0.0498 0.0202 1.0000
11.000 1.3359 0.04658 0.03807 -0.0476 0.0197 1.0000
11.250 1.3325 0.04935 0.04108 -0.0458 0.0192 1.0000
11.500 1.3290 0.05234 0.04425 -0.0445 0.0186 1.0000
11.750 1.3251 0.05555 0.04765 -0.0437 0.0180 1.0000
12.000 1.3209 0.05899 0.05126 -0.0431 0.0174 1.0000
12.250 1.3164 0.06265 0.05508 -0.0430 0.0169 1.0000
12.500 1.3118 0.06651 0.05911 -0.0431 0.0166 1.0000
12.750 1.3072 0.07051 0.06328 -0.0434 0.0163 1.0000
13.000 1.3025 0.07468 0.06763 -0.0439 0.0161 1.0000
13.250 1.2971 0.07910 0.07223 -0.0447 0.0159 1.0000
13.500 1.2908 0.08377 0.07708 -0.0458 0.0157 1.0000
13.750 1.2834 0.08874 0.08225 -0.0472 0.0156 1.0000
14.000 1.2749 0.09407 0.08777 -0.0491 0.0155 1.0000
14.250 1.2652 0.09978 0.09368 -0.0514 0.0154 1.0000
14.500 1.2545 0.10586 0.09996 -0.0542 0.0154 1.0000
14.750 1.2428 0.11239 0.10669 -0.0575 0.0154 1.0000
15.000 1.2302 0.11937 0.11387 -0.0613 0.0154 1.0000
15.250 1.2165 0.12686 0.12155 -0.0656 0.0155 1.0000
15.500 1.2018 0.13502 0.12990 -0.0705 0.0156 1.0000
15.750 1.1857 0.14411 0.13917 -0.0763 0.0157 1.0000
16.000 1.1683 0.15434 0.14958 -0.0829 0.0160 1.0000
16.250 1.1479 0.16648 0.16187 -0.0906 0.0164 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 276 (DAIMLER VII) AIRFOIL (goe276-il)