GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Reynolds number: 1,000,000 Max Cl/Cd: 98.18 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe281-il-1000000-n5.txt Download as CSV file: xf-goe281-il-1000000-n5.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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3237 0.08660 0.08505 -0.0341 0.9719 0.0049
-8.000 -0.3186 0.08301 0.08146 -0.0364 0.9605 0.0051
-7.750 -0.3130 0.07910 0.07753 -0.0397 0.9490 0.0053
-7.500 -0.3038 0.07397 0.07236 -0.0451 0.9373 0.0056
-7.250 -0.2928 0.06564 0.06398 -0.0548 0.9245 0.0062
-7.000 -0.2739 0.06239 0.06068 -0.0588 0.9124 0.0064
-6.750 -0.2536 0.05933 0.05755 -0.0625 0.8990 0.0067
-6.500 -0.2318 0.05579 0.05392 -0.0666 0.8836 0.0071
-6.250 -0.2074 0.04986 0.04782 -0.0730 0.8663 0.0078
-6.000 -0.1796 0.04169 0.03938 -0.0804 0.8491 0.0089
-5.750 -0.1545 0.03938 0.03690 -0.0822 0.8301 0.0092
-5.500 -0.1286 0.03671 0.03405 -0.0841 0.8119 0.0097
-5.250 -0.0989 0.02827 0.02510 -0.0881 0.7982 0.0119
-5.000 -0.0727 0.02722 0.02390 -0.0885 0.7818 0.0122
-4.750 -0.0462 0.02590 0.02241 -0.0890 0.7656 0.0126
-4.500 -0.0169 0.01894 0.01472 -0.0900 0.7512 0.0157
-4.250 0.0100 0.01852 0.01416 -0.0902 0.7329 0.0160
-4.000 0.0371 0.01809 0.01359 -0.0904 0.7149 0.0163
-3.750 0.0644 0.01775 0.01312 -0.0906 0.6980 0.0167
-3.500 0.0920 0.01689 0.01206 -0.0907 0.6828 0.0174
-3.250 0.1203 0.01552 0.01042 -0.0908 0.6690 0.0184
-3.000 0.1490 0.01438 0.00897 -0.0908 0.6579 0.0198
-2.750 0.1774 0.01383 0.00822 -0.0909 0.6477 0.0202
-2.500 0.2056 0.01351 0.00774 -0.0910 0.6367 0.0204
-2.250 0.2338 0.01239 0.00639 -0.0912 0.6265 0.0207
-2.000 0.2618 0.01153 0.00540 -0.0913 0.6169 0.0209
-1.750 0.2900 0.01108 0.00489 -0.0915 0.6090 0.0213
-1.250 0.3465 0.01026 0.00393 -0.0918 0.5919 0.0217
-1.000 0.3747 0.00996 0.00356 -0.0919 0.5834 0.0219
-0.750 0.4029 0.00972 0.00327 -0.0920 0.5710 0.0223
-0.500 0.4310 0.00953 0.00302 -0.0921 0.5560 0.0229
-0.250 0.4590 0.00938 0.00279 -0.0921 0.5369 0.0235
0.000 0.4865 0.00933 0.00261 -0.0921 0.5017 0.0240
0.250 0.5135 0.00939 0.00248 -0.0921 0.4613 0.0244
0.500 0.5408 0.00942 0.00238 -0.0921 0.4355 0.0247
0.750 0.5684 0.00942 0.00229 -0.0922 0.4166 0.0250
1.000 0.5963 0.00939 0.00221 -0.0923 0.4040 0.0252
1.250 0.6242 0.00939 0.00217 -0.0924 0.3948 0.0256
1.500 0.6523 0.00936 0.00212 -0.0925 0.3872 0.0259
1.750 0.6803 0.00933 0.00207 -0.0926 0.3795 0.0259
2.000 0.7084 0.00930 0.00202 -0.0927 0.3725 0.0259
2.250 0.7363 0.00932 0.00201 -0.0928 0.3632 0.0260
2.500 0.7641 0.00936 0.00201 -0.0928 0.3513 0.0261
2.750 0.7918 0.00942 0.00204 -0.0929 0.3385 0.0264
3.000 0.8190 0.00956 0.00210 -0.0929 0.3180 0.0267
3.250 0.8456 0.00978 0.00218 -0.0928 0.2867 0.0277
3.500 0.8721 0.01002 0.00230 -0.0928 0.2615 0.0301
3.750 0.8983 0.01030 0.00247 -0.0926 0.2364 0.0317
4.000 0.9243 0.01060 0.00266 -0.0925 0.2128 0.0331
4.250 0.9506 0.01085 0.00285 -0.0924 0.1952 0.0349
4.500 0.9769 0.01105 0.00306 -0.0923 0.1784 0.1052
5.000 1.0221 0.01041 0.00383 -0.0912 0.1153 1.0000
5.250 1.0472 0.01082 0.00414 -0.0910 0.0966 1.0000
5.500 1.0666 0.01200 0.00492 -0.0898 0.0207 1.0000
5.750 1.0922 0.01230 0.00520 -0.0896 0.0150 1.0000
6.000 1.1180 0.01256 0.00549 -0.0894 0.0127 1.0000
6.250 1.1435 0.01286 0.00582 -0.0891 0.0111 1.0000
6.500 1.1684 0.01322 0.00620 -0.0887 0.0096 1.0000
6.750 1.1928 0.01361 0.00663 -0.0883 0.0085 1.0000
7.000 1.2176 0.01394 0.00699 -0.0879 0.0078 1.0000
7.250 1.2419 0.01430 0.00738 -0.0875 0.0071 1.0000
7.500 1.2658 0.01470 0.00779 -0.0870 0.0064 1.0000
7.750 1.2882 0.01526 0.00840 -0.0863 0.0057 1.0000
8.000 1.3116 0.01568 0.00886 -0.0857 0.0055 1.0000
8.250 1.3343 0.01615 0.00939 -0.0850 0.0051 1.0000
8.500 1.3564 0.01666 0.00994 -0.0843 0.0048 1.0000
8.750 1.3781 0.01717 0.01049 -0.0835 0.0045 1.0000
9.000 1.3996 0.01768 0.01103 -0.0827 0.0042 1.0000
9.250 1.4196 0.01830 0.01169 -0.0816 0.0039 1.0000
9.500 1.4377 0.01907 0.01255 -0.0803 0.0037 1.0000
9.750 1.4565 0.01972 0.01327 -0.0791 0.0035 1.0000
10.000 1.4740 0.02044 0.01406 -0.0777 0.0034 1.0000
10.250 1.4899 0.02121 0.01492 -0.0761 0.0032 1.0000
10.500 1.5041 0.02202 0.01581 -0.0742 0.0031 1.0000
10.750 1.5155 0.02287 0.01674 -0.0718 0.0030 1.0000
11.000 1.5246 0.02375 0.01770 -0.0691 0.0029 1.0000
11.250 1.5334 0.02471 0.01875 -0.0666 0.0028 1.0000
11.500 1.5416 0.02577 0.01989 -0.0642 0.0027 1.0000
11.750 1.5494 0.02690 0.02110 -0.0619 0.0026 1.0000
12.000 1.5559 0.02820 0.02249 -0.0597 0.0026 1.0000
12.250 1.5613 0.02964 0.02402 -0.0577 0.0025 1.0000
12.500 1.5645 0.03137 0.02584 -0.0556 0.0024 1.0000
12.750 1.5644 0.03349 0.02807 -0.0537 0.0024 1.0000
13.000 1.5588 0.03632 0.03104 -0.0519 0.0023 1.0000
13.250 1.5506 0.03965 0.03451 -0.0504 0.0023 1.0000
13.500 1.5492 0.04248 0.03748 -0.0497 0.0022 1.0000
13.750 1.5459 0.04569 0.04081 -0.0493 0.0022 1.0000
14.000 1.5412 0.04924 0.04449 -0.0492 0.0022 1.0000
14.250 1.5361 0.05300 0.04838 -0.0494 0.0022 1.0000
14.500 1.5280 0.05724 0.05275 -0.0498 0.0022 1.0000
14.750 1.5206 0.06153 0.05717 -0.0504 0.0021 1.0000
15.000 1.5113 0.06626 0.06203 -0.0514 0.0021 1.0000
15.250 1.5007 0.07131 0.06721 -0.0526 0.0021 1.0000
15.500 1.4893 0.07668 0.07271 -0.0540 0.0020 1.0000
15.750 1.4777 0.08230 0.07846 -0.0558 0.0020 1.0000
16.000 1.4655 0.08811 0.08439 -0.0577 0.0020 1.0000
16.250 1.4533 0.09400 0.09041 -0.0597 0.0020 1.0000
16.500 1.4402 0.10014 0.09666 -0.0619 0.0019 1.0000
16.750 1.4272 0.10635 0.10300 -0.0642 0.0019 1.0000
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Polar data table (+)
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