GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 276 (DAIMLER VII) AIRFOIL (goe276-il) Reynolds number: 500,000 Max Cl/Cd: 93.6 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe276-il-500000-n5.txt Download as CSV file: xf-goe276-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3845 0.09041 0.08823 -0.0200 1.0000 0.0083
-7.750 -0.3896 0.08774 0.08560 -0.0194 1.0000 0.0084
-7.500 -0.3896 0.08443 0.08233 -0.0206 1.0000 0.0085
-7.250 -0.3774 0.07961 0.07752 -0.0260 0.9979 0.0088
-7.000 -0.3540 0.07236 0.07023 -0.0364 0.9932 0.0093
-6.750 -0.3278 0.06728 0.06512 -0.0442 0.9880 0.0099
-6.500 -0.3019 0.06414 0.06194 -0.0491 0.9814 0.0104
-6.250 -0.2733 0.05931 0.05704 -0.0561 0.9730 0.0109
-6.000 -0.2395 0.05315 0.05077 -0.0645 0.9647 0.0116
-5.750 -0.1989 0.04387 0.04122 -0.0754 0.9551 0.0131
-5.500 -0.1667 0.04221 0.03949 -0.0785 0.9464 0.0137
-5.250 -0.1296 0.03843 0.03554 -0.0834 0.9376 0.0148
-5.000 -0.0853 0.02935 0.02585 -0.0902 0.9281 0.0176
-4.750 -0.0548 0.02861 0.02501 -0.0918 0.9156 0.0181
-4.500 -0.0255 0.02701 0.02322 -0.0929 0.9024 0.0189
-4.250 0.0038 0.02478 0.02071 -0.0938 0.8887 0.0200
-4.000 0.0346 0.02198 0.01749 -0.0943 0.8765 0.0222
-3.750 0.0642 0.02032 0.01548 -0.0944 0.8660 0.0231
-3.500 0.0924 0.01785 0.01267 -0.0953 0.8564 0.0244
-3.250 0.1198 0.01727 0.01198 -0.0955 0.8462 0.0252
-3.000 0.1477 0.01641 0.01095 -0.0956 0.8353 0.0258
-2.750 0.1759 0.01548 0.00980 -0.0957 0.8228 0.0264
-2.500 0.2043 0.01457 0.00870 -0.0957 0.8103 0.0268
-2.250 0.2327 0.01376 0.00770 -0.0957 0.7973 0.0272
-2.000 0.2608 0.01318 0.00697 -0.0957 0.7818 0.0279
-1.750 0.2886 0.01256 0.00616 -0.0955 0.7593 0.0283
-1.500 0.3154 0.01204 0.00538 -0.0951 0.7153 0.0284
-1.250 0.3395 0.01193 0.00477 -0.0942 0.6221 0.0287
-1.000 0.3643 0.01197 0.00436 -0.0936 0.5341 0.0292
-0.750 0.3906 0.01192 0.00402 -0.0934 0.4799 0.0298
-0.500 0.4179 0.01178 0.00374 -0.0933 0.4573 0.0304
-0.250 0.4457 0.01162 0.00350 -0.0933 0.4436 0.0309
0.000 0.4734 0.01150 0.00330 -0.0933 0.4320 0.0313
0.250 0.5012 0.01140 0.00313 -0.0933 0.4203 0.0316
0.750 0.5568 0.01133 0.00299 -0.0934 0.4013 0.0326
1.000 0.5848 0.01120 0.00281 -0.0934 0.3945 0.0329
1.250 0.6131 0.01108 0.00269 -0.0935 0.3886 0.0330
1.500 0.6412 0.01102 0.00260 -0.0936 0.3827 0.0333
1.750 0.6692 0.01099 0.00253 -0.0937 0.3773 0.0339
2.000 0.6973 0.01097 0.00251 -0.0937 0.3712 0.0351
2.250 0.7251 0.01101 0.00251 -0.0937 0.3648 0.0375
2.500 0.7530 0.01104 0.00255 -0.0937 0.3567 0.0417
3.000 0.8022 0.00932 0.00283 -0.0928 0.3406 1.0000
3.250 0.8298 0.00946 0.00292 -0.0928 0.3325 1.0000
3.500 0.8572 0.00961 0.00304 -0.0927 0.3226 1.0000
3.750 0.8846 0.00978 0.00316 -0.0927 0.3102 1.0000
4.000 0.9117 0.00996 0.00329 -0.0926 0.2969 1.0000
4.250 0.9386 0.01016 0.00344 -0.0925 0.2840 1.0000
4.500 0.9654 0.01038 0.00363 -0.0924 0.2716 1.0000
4.750 0.9921 0.01062 0.00382 -0.0922 0.2597 1.0000
5.000 1.0184 0.01088 0.00404 -0.0920 0.2470 1.0000
5.250 1.0444 0.01119 0.00430 -0.0918 0.2298 1.0000
5.500 1.0695 0.01163 0.00460 -0.0915 0.2048 1.0000
5.750 1.0944 0.01209 0.00492 -0.0911 0.1753 1.0000
6.000 1.1183 0.01267 0.00531 -0.0907 0.1398 1.0000
6.250 1.1427 0.01319 0.00573 -0.0903 0.1212 1.0000
6.500 1.1674 0.01364 0.00613 -0.0899 0.1084 1.0000
6.750 1.1919 0.01410 0.00655 -0.0895 0.0931 1.0000
7.000 1.2090 0.01563 0.00761 -0.0881 0.0210 1.0000
7.250 1.2323 0.01623 0.00823 -0.0874 0.0150 1.0000
7.500 1.2564 0.01669 0.00877 -0.0868 0.0131 1.0000
7.750 1.2799 0.01721 0.00937 -0.0862 0.0117 1.0000
8.000 1.3022 0.01785 0.01008 -0.0854 0.0103 1.0000
8.250 1.3237 0.01860 0.01093 -0.0845 0.0092 1.0000
8.500 1.3457 0.01921 0.01164 -0.0836 0.0086 1.0000
8.750 1.3668 0.01989 0.01242 -0.0827 0.0081 1.0000
9.000 1.3871 0.02064 0.01326 -0.0816 0.0076 1.0000
9.250 1.4064 0.02143 0.01413 -0.0804 0.0071 1.0000
9.500 1.4236 0.02239 0.01517 -0.0789 0.0066 1.0000
9.750 1.4386 0.02351 0.01640 -0.0771 0.0062 1.0000
10.000 1.4556 0.02434 0.01735 -0.0756 0.0059 1.0000
10.250 1.4699 0.02535 0.01848 -0.0737 0.0057 1.0000
10.500 1.4820 0.02643 0.01968 -0.0715 0.0054 1.0000
10.750 1.4920 0.02756 0.02092 -0.0690 0.0052 1.0000
11.000 1.4986 0.02874 0.02220 -0.0660 0.0051 1.0000
11.250 1.5026 0.02998 0.02355 -0.0627 0.0049 1.0000
11.500 1.5057 0.03139 0.02507 -0.0596 0.0048 1.0000
11.750 1.5078 0.03298 0.02677 -0.0568 0.0047 1.0000
12.000 1.5082 0.03485 0.02876 -0.0542 0.0046 1.0000
12.250 1.5062 0.03710 0.03115 -0.0519 0.0045 1.0000
12.500 1.5008 0.03986 0.03406 -0.0499 0.0044 1.0000
12.750 1.4919 0.04327 0.03761 -0.0483 0.0043 1.0000
13.000 1.4857 0.04665 0.04114 -0.0474 0.0042 1.0000
13.250 1.4809 0.05013 0.04478 -0.0471 0.0042 1.0000
13.500 1.4758 0.05395 0.04876 -0.0474 0.0041 1.0000
13.750 1.4691 0.05825 0.05322 -0.0481 0.0041 1.0000
14.000 1.4606 0.06310 0.05824 -0.0494 0.0040 1.0000
14.250 1.4521 0.06822 0.06351 -0.0512 0.0040 1.0000
14.500 1.4427 0.07360 0.06905 -0.0531 0.0039 1.0000
14.750 1.4327 0.07922 0.07482 -0.0553 0.0039 1.0000
15.000 1.4212 0.08512 0.08087 -0.0575 0.0038 1.0000
15.250 1.4095 0.09103 0.08692 -0.0598 0.0038 1.0000
15.500 1.3965 0.09721 0.09324 -0.0622 0.0038 1.0000
15.750 1.3848 0.10330 0.09946 -0.0648 0.0037 1.0000
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Polar data table (+)
Polar graphs
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