GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Reynolds number: 200,000 Max Cl/Cd: 73.21 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe276-il-200000-n5.txt Download as CSV file: xf-goe276-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3713 0.10016 0.09666 -0.0220 1.0000 0.0227
-8.000 -0.3742 0.09781 0.09439 -0.0227 1.0000 0.0228
-7.750 -0.3737 0.09501 0.09164 -0.0245 1.0000 0.0229
-7.500 -0.3692 0.09176 0.08843 -0.0270 1.0000 0.0230
-7.250 -0.3635 0.08827 0.08496 -0.0292 1.0000 0.0230
-7.000 -0.3573 0.08469 0.08140 -0.0310 1.0000 0.0230
-6.750 -0.3511 0.08110 0.07783 -0.0326 1.0000 0.0230
-6.500 -0.3459 0.07759 0.07434 -0.0334 1.0000 0.0230
-6.250 -0.3347 0.07334 0.07009 -0.0342 0.9980 0.0225
-6.000 -0.3119 0.06845 0.06517 -0.0387 0.9944 0.0217
-5.000 -0.1634 0.04988 0.04597 -0.0677 0.9750 0.0316
-4.500 -0.0965 0.04025 0.03594 -0.0766 0.9658 0.0307
-4.250 -0.0607 0.03617 0.03155 -0.0800 0.9588 0.0310
-4.000 -0.0292 0.03391 0.02922 -0.0831 0.9538 0.0373
-3.750 0.0063 0.03095 0.02597 -0.0857 0.9455 0.0388
-3.500 0.0478 0.02709 0.02161 -0.0889 0.9400 0.0364
-3.250 0.0816 0.02541 0.01972 -0.0907 0.9323 0.0396
-3.000 0.1199 0.02300 0.01693 -0.0929 0.9260 0.0389
-2.750 0.1558 0.02099 0.01454 -0.0945 0.9169 0.0383
-2.500 0.1918 0.01941 0.01264 -0.0960 0.9071 0.0384
-2.250 0.2253 0.01837 0.01136 -0.0970 0.8970 0.0404
-2.000 0.2566 0.01726 0.01000 -0.0975 0.8869 0.0402
-1.750 0.2873 0.01628 0.00880 -0.0978 0.8762 0.0398
-1.500 0.3171 0.01546 0.00779 -0.0978 0.8642 0.0397
-1.250 0.3458 0.01478 0.00695 -0.0977 0.8511 0.0399
-1.000 0.3739 0.01421 0.00624 -0.0974 0.8367 0.0404
-0.750 0.4014 0.01372 0.00566 -0.0971 0.8200 0.0409
-0.500 0.4286 0.01331 0.00517 -0.0966 0.7995 0.0416
-0.250 0.4552 0.01307 0.00482 -0.0961 0.7700 0.0436
0.000 0.4811 0.01288 0.00445 -0.0953 0.7214 0.0446
0.250 0.5052 0.01280 0.00401 -0.0941 0.6459 0.0446
0.500 0.5293 0.01288 0.00375 -0.0932 0.5831 0.0448
0.750 0.5546 0.01296 0.00359 -0.0927 0.5364 0.0450
1.000 0.5806 0.01305 0.00348 -0.0923 0.5038 0.0454
1.250 0.6071 0.01309 0.00337 -0.0921 0.4824 0.0464
1.500 0.6339 0.01317 0.00331 -0.0919 0.4662 0.0485
1.750 0.6607 0.01329 0.00332 -0.0917 0.4525 0.0518
2.000 0.6875 0.01343 0.00337 -0.0915 0.4401 0.0575
2.250 0.7069 0.01177 0.00361 -0.0901 0.4299 0.8434
3.250 0.8152 0.01249 0.00408 -0.0893 0.3928 1.0000
3.500 0.8422 0.01269 0.00426 -0.0892 0.3831 1.0000
3.750 0.8691 0.01290 0.00447 -0.0891 0.3745 1.0000
4.000 0.8958 0.01313 0.00467 -0.0889 0.3654 1.0000
4.250 0.9227 0.01332 0.00489 -0.0887 0.3551 1.0000
4.500 0.9493 0.01354 0.00513 -0.0885 0.3450 1.0000
4.750 0.9756 0.01378 0.00537 -0.0883 0.3352 1.0000
5.000 1.0021 0.01399 0.00563 -0.0881 0.3241 1.0000
5.250 1.0284 0.01423 0.00592 -0.0878 0.3127 1.0000
5.500 1.0544 0.01449 0.00621 -0.0876 0.3008 1.0000
5.750 1.0800 0.01478 0.00652 -0.0872 0.2885 1.0000
6.000 1.1054 0.01510 0.00686 -0.0869 0.2750 1.0000
6.250 1.1296 0.01551 0.00723 -0.0864 0.2526 1.0000
6.500 1.1530 0.01603 0.00764 -0.0858 0.2258 1.0000
6.750 1.1763 0.01657 0.00811 -0.0852 0.2028 1.0000
7.000 1.1994 0.01715 0.00861 -0.0846 0.1753 1.0000
7.250 1.2216 0.01783 0.00921 -0.0839 0.1463 1.0000
7.500 1.2419 0.01876 0.00995 -0.0830 0.1162 1.0000
8.000 1.2738 0.02174 0.01235 -0.0800 0.0246 1.0000
8.250 1.2927 0.02277 0.01345 -0.0787 0.0194 1.0000
8.500 1.3116 0.02374 0.01457 -0.0774 0.0173 1.0000
8.750 1.3288 0.02485 0.01588 -0.0758 0.0157 1.0000
9.000 1.3428 0.02624 0.01748 -0.0738 0.0145 1.0000
9.250 1.3560 0.02754 0.01896 -0.0718 0.0136 1.0000
9.500 1.3697 0.02869 0.02028 -0.0698 0.0127 1.0000
9.750 1.3800 0.03003 0.02178 -0.0675 0.0120 1.0000
10.000 1.3868 0.03151 0.02341 -0.0647 0.0116 1.0000
10.250 1.3895 0.03304 0.02508 -0.0613 0.0112 1.0000
10.500 1.3902 0.03472 0.02693 -0.0578 0.0109 1.0000
10.750 1.3903 0.03660 0.02894 -0.0547 0.0106 1.0000
11.000 1.3894 0.03871 0.03118 -0.0520 0.0104 1.0000
11.250 1.3878 0.04106 0.03366 -0.0496 0.0102 1.0000
11.500 1.3850 0.04370 0.03642 -0.0476 0.0099 1.0000
11.750 1.3805 0.04673 0.03956 -0.0458 0.0096 1.0000
12.000 1.3742 0.05025 0.04320 -0.0441 0.0094 1.0000
12.250 1.3748 0.05293 0.04606 -0.0434 0.0091 1.0000
12.500 1.3737 0.05597 0.04930 -0.0430 0.0089 1.0000
12.750 1.3712 0.05935 0.05287 -0.0428 0.0086 1.0000
13.000 1.3673 0.06308 0.05679 -0.0429 0.0084 1.0000
13.250 1.3622 0.06713 0.06102 -0.0434 0.0083 1.0000
13.500 1.3560 0.07152 0.06561 -0.0442 0.0082 1.0000
13.750 1.3488 0.07624 0.07051 -0.0454 0.0081 1.0000
14.000 1.3404 0.08127 0.07573 -0.0470 0.0081 1.0000
14.250 1.3309 0.08665 0.08131 -0.0489 0.0080 1.0000
14.500 1.3206 0.09237 0.08722 -0.0513 0.0079 1.0000
14.750 1.3095 0.09843 0.09346 -0.0540 0.0079 1.0000
15.000 1.2975 0.10477 0.09999 -0.0570 0.0079 1.0000
15.250 1.2850 0.11141 0.10684 -0.0604 0.0079 1.0000
15.500 1.2721 0.11836 0.11397 -0.0641 0.0079 1.0000
15.750 1.2587 0.12563 0.12137 -0.0681 0.0079 1.0000
16.000 1.2453 0.13321 0.12913 -0.0726 0.0079 1.0000
16.250 1.2317 0.14125 0.13732 -0.0774 0.0079 1.0000
16.500 1.2179 0.14977 0.14601 -0.0827 0.0080 1.0000
16.750 1.2039 0.15885 0.15524 -0.0885 0.0080 1.0000
17.000 1.1895 0.16857 0.16510 -0.0947 0.0081 1.0000
17.250 1.1744 0.17924 0.17589 -0.1014 0.0083 1.0000
17.500 1.1581 0.19126 0.18800 -0.1089 0.0085 1.0000
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Polar data table (+)
Polar graphs
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