GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Reynolds number: 200,000 Max Cl/Cd: 79.06 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe281-il-200000.txt Download as CSV file: xf-goe281-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 281 (DAIMLER XII) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3436 0.10423 0.10082 -0.0296 1.0000 0.0263
-8.250 -0.3465 0.10202 0.09867 -0.0305 1.0000 0.0263
-8.000 -0.3474 0.09955 0.09626 -0.0320 1.0000 0.0264
-7.750 -0.3469 0.09686 0.09361 -0.0338 1.0000 0.0264
-7.500 -0.3467 0.09189 0.08870 -0.0302 1.0000 0.0268
-7.250 -0.3443 0.08860 0.08544 -0.0270 1.0000 0.0272
-7.000 -0.3447 0.08604 0.08292 -0.0255 1.0000 0.0276
-6.750 -0.3462 0.08368 0.08060 -0.0246 1.0000 0.0280
-6.500 -0.3478 0.08137 0.07833 -0.0240 1.0000 0.0284
-6.250 -0.3489 0.07906 0.07606 -0.0236 1.0000 0.0289
-6.000 -0.3488 0.07672 0.07374 -0.0236 1.0000 0.0297
-5.750 -0.3382 0.07359 0.07061 -0.0264 0.9989 0.0311
-5.500 -0.2660 0.06734 0.06402 -0.0469 0.9929 0.0339
-5.250 -0.2330 0.06038 0.05695 -0.0540 0.9878 0.0346
-5.000 -0.2078 0.05616 0.05276 -0.0567 0.9842 0.0359
-4.750 -0.1737 0.05232 0.04885 -0.0616 0.9785 0.0379
-4.500 -0.1069 0.04921 0.04506 -0.0722 0.9731 0.0441
-4.250 -0.0793 0.04261 0.03856 -0.0766 0.9703 0.0462
-4.000 -0.0478 0.03980 0.03569 -0.0795 0.9633 0.0493
-3.750 0.0038 0.03629 0.03155 -0.0854 0.9591 0.0576
-3.500 0.0404 0.03304 0.02841 -0.0895 0.9565 0.0620
-3.250 0.0792 0.03050 0.02548 -0.0925 0.9489 0.0727
-1.500 0.2944 0.01929 0.01363 -0.1005 0.8864 0.2488
-1.250 0.3196 0.01817 0.01255 -0.0998 0.8740 0.2864
-1.000 0.3508 0.01700 0.01112 -0.0996 0.8618 0.2873
-0.750 0.3996 0.01552 0.00815 -0.0973 0.8520 0.0815
-0.500 0.4279 0.01461 0.00703 -0.0965 0.8405 0.0735
-0.250 0.4555 0.01439 0.00665 -0.0957 0.8271 0.0695
0.000 0.4821 0.01362 0.00584 -0.0950 0.8129 0.0674
0.250 0.5087 0.01312 0.00530 -0.0942 0.7981 0.0659
0.500 0.5353 0.01274 0.00487 -0.0936 0.7831 0.0652
0.750 0.5620 0.01245 0.00454 -0.0930 0.7674 0.0654
1.000 0.5887 0.01224 0.00428 -0.0925 0.7511 0.0664
1.250 0.6155 0.01215 0.00410 -0.0921 0.7349 0.0699
1.500 0.6426 0.01203 0.00390 -0.0917 0.7193 0.0737
1.750 0.6696 0.01200 0.00380 -0.0913 0.7039 0.0786
2.000 0.6965 0.01182 0.00378 -0.0909 0.6884 0.1688
2.250 0.7203 0.01018 0.00383 -0.0899 0.6732 1.0000
2.500 0.7469 0.01037 0.00385 -0.0894 0.6564 1.0000
2.750 0.7731 0.01057 0.00389 -0.0889 0.6381 1.0000
3.000 0.7992 0.01076 0.00397 -0.0885 0.6170 1.0000
3.250 0.8252 0.01097 0.00405 -0.0880 0.5963 1.0000
3.500 0.8512 0.01117 0.00418 -0.0876 0.5752 1.0000
3.750 0.8770 0.01136 0.00429 -0.0871 0.5532 1.0000
4.000 0.9027 0.01155 0.00441 -0.0867 0.5304 1.0000
4.250 0.9282 0.01179 0.00455 -0.0862 0.5081 1.0000
4.500 0.9535 0.01206 0.00476 -0.0858 0.4864 1.0000
4.750 0.9784 0.01240 0.00499 -0.0852 0.4659 1.0000
5.000 1.0031 0.01278 0.00528 -0.0847 0.4469 1.0000
5.250 1.0274 0.01319 0.00561 -0.0842 0.4249 1.0000
5.500 1.0509 0.01362 0.00597 -0.0835 0.3982 1.0000
5.750 1.0745 0.01402 0.00630 -0.0829 0.3719 1.0000
6.000 1.0983 0.01439 0.00664 -0.0823 0.3472 1.0000
6.250 1.1213 0.01478 0.00695 -0.0816 0.3123 1.0000
6.500 1.1427 0.01536 0.00737 -0.0808 0.2755 1.0000
6.750 1.1639 0.01601 0.00787 -0.0799 0.2448 1.0000
7.000 1.1848 0.01670 0.00843 -0.0790 0.2158 1.0000
7.250 1.2053 0.01743 0.00901 -0.0781 0.1796 1.0000
7.500 1.2235 0.01842 0.00967 -0.0768 0.1308 1.0000
7.750 1.2404 0.01956 0.01056 -0.0754 0.0903 1.0000
8.000 1.2501 0.02146 0.01201 -0.0729 0.0345 1.0000
8.250 1.2685 0.02237 0.01305 -0.0714 0.0310 1.0000
8.500 1.2853 0.02339 0.01424 -0.0698 0.0287 1.0000
8.750 1.2991 0.02465 0.01566 -0.0678 0.0264 1.0000
9.000 1.3101 0.02602 0.01723 -0.0654 0.0252 1.0000
9.250 1.3164 0.02760 0.01902 -0.0624 0.0246 1.0000
9.500 1.3207 0.02902 0.02056 -0.0591 0.0244 1.0000
9.750 1.3243 0.03055 0.02221 -0.0559 0.0242 1.0000
10.000 1.3274 0.03225 0.02402 -0.0530 0.0240 1.0000
10.250 1.3307 0.03410 0.02596 -0.0503 0.0239 1.0000
10.500 1.3352 0.03604 0.02799 -0.0479 0.0238 1.0000
10.750 1.3416 0.03800 0.03004 -0.0458 0.0236 1.0000
11.000 1.3495 0.03991 0.03205 -0.0439 0.0232 1.0000
11.250 1.3580 0.04186 0.03415 -0.0422 0.0226 1.0000
11.500 1.3685 0.04393 0.03633 -0.0405 0.0223 1.0000
11.750 1.3813 0.04619 0.03873 -0.0389 0.0225 1.0000
12.000 1.3939 0.04874 0.04145 -0.0374 0.0229 1.0000
12.250 1.4063 0.05177 0.04469 -0.0359 0.0234 1.0000
12.500 1.4410 0.05608 0.04914 -0.0360 0.0249 1.0000
12.750 1.4379 0.05736 0.05065 -0.0336 0.0255 1.0000
13.000 1.4286 0.05955 0.05325 -0.0313 0.0268 1.0000
13.250 1.4118 0.06403 0.05824 -0.0295 0.0289 1.0000
13.500 1.4001 0.06914 0.06367 -0.0286 0.0308 1.0000
13.750 1.4021 0.07310 0.06806 -0.0273 0.0359 1.0000
14.000 1.3729 0.07925 0.07458 -0.0283 0.0370 1.0000
14.250 1.3471 0.08581 0.08144 -0.0301 0.0379 1.0000
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Polar data table (+)
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