GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.14 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe277-il-1000000-n5.txt Download as CSV file: xf-goe277-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 277 (DAIMLER VIII) 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4051 0.11398 0.11233 -0.0136 1.0000 0.0051
-10.250 -0.4077 0.10821 0.10657 -0.0158 1.0000 0.0054
-10.000 -0.4059 0.10396 0.10233 -0.0177 1.0000 0.0056
-9.750 -0.3995 0.10098 0.09937 -0.0191 1.0000 0.0057
-9.500 -0.3930 0.09804 0.09644 -0.0206 1.0000 0.0058
-9.250 -0.3869 0.09505 0.09347 -0.0221 1.0000 0.0060
-8.750 -0.3789 0.08843 0.08688 -0.0254 1.0000 0.0065
-7.250 -0.3067 0.04706 0.04515 -0.0738 0.9261 0.0103
-7.000 -0.2840 0.04433 0.04232 -0.0762 0.9141 0.0107
-6.750 -0.2661 0.02575 0.02287 -0.0869 0.9041 0.0138
-6.250 -0.2245 0.01453 0.01036 -0.0881 0.8786 0.0179
-6.000 -0.1983 0.01390 0.00954 -0.0879 0.8605 0.0184
-5.750 -0.1715 0.01392 0.00947 -0.0876 0.8356 0.0188
-5.500 -0.1453 0.01408 0.00946 -0.0872 0.7934 0.0191
-5.250 -0.1189 0.01438 0.00958 -0.0868 0.7511 0.0194
-5.000 -0.0919 0.01446 0.00954 -0.0866 0.7262 0.0198
-4.750 -0.0644 0.01421 0.00916 -0.0866 0.7116 0.0203
-4.500 -0.0369 0.01389 0.00871 -0.0866 0.6990 0.0210
-4.250 -0.0093 0.01330 0.00795 -0.0866 0.6863 0.0217
-4.000 0.0184 0.01274 0.00723 -0.0866 0.6724 0.0223
-3.750 0.0461 0.01239 0.00674 -0.0866 0.6568 0.0229
-3.500 0.0739 0.01198 0.00618 -0.0866 0.6406 0.0233
-3.250 0.1017 0.01158 0.00564 -0.0866 0.6229 0.0235
-3.000 0.1294 0.01121 0.00513 -0.0865 0.6022 0.0237
-2.750 0.1570 0.01092 0.00469 -0.0865 0.5801 0.0239
-2.500 0.1847 0.01067 0.00429 -0.0864 0.5577 0.0240
-2.250 0.2123 0.01052 0.00402 -0.0864 0.5367 0.0242
-2.000 0.2398 0.00994 0.00329 -0.0864 0.5187 0.0248
-1.750 0.2674 0.00950 0.00274 -0.0864 0.5037 0.0254
-1.500 0.2953 0.00929 0.00245 -0.0864 0.4897 0.0261
-1.250 0.3233 0.00917 0.00227 -0.0864 0.4756 0.0267
-1.000 0.3513 0.00910 0.00214 -0.0864 0.4611 0.0273
-0.750 0.3793 0.00905 0.00201 -0.0864 0.4460 0.0278
-0.500 0.4072 0.00901 0.00190 -0.0865 0.4296 0.0282
-0.250 0.4351 0.00900 0.00181 -0.0865 0.4112 0.0287
0.000 0.4629 0.00901 0.00173 -0.0865 0.3930 0.0290
0.250 0.4907 0.00903 0.00167 -0.0865 0.3776 0.0294
0.500 0.5187 0.00904 0.00162 -0.0865 0.3659 0.0297
0.750 0.5466 0.00907 0.00160 -0.0865 0.3559 0.0303
1.000 0.5746 0.00909 0.00159 -0.0865 0.3473 0.0310
1.250 0.6026 0.00912 0.00158 -0.0865 0.3405 0.0315
1.500 0.6306 0.00915 0.00158 -0.0865 0.3342 0.0321
1.750 0.6584 0.00920 0.00161 -0.0866 0.3282 0.0330
2.000 0.6864 0.00924 0.00163 -0.0866 0.3225 0.0362
3.000 0.7924 0.00767 0.00212 -0.0862 0.2991 1.0000
3.250 0.8203 0.00777 0.00221 -0.0862 0.2961 1.0000
3.500 0.8481 0.00787 0.00230 -0.0862 0.2924 1.0000
3.750 0.8757 0.00800 0.00240 -0.0862 0.2884 1.0000
4.000 0.9032 0.00813 0.00252 -0.0862 0.2848 1.0000
4.250 0.9309 0.00824 0.00263 -0.0862 0.2816 1.0000
4.500 0.9584 0.00836 0.00274 -0.0862 0.2766 1.0000
4.750 0.9858 0.00851 0.00288 -0.0861 0.2723 1.0000
5.000 1.0130 0.00865 0.00301 -0.0861 0.2660 1.0000
5.250 1.0399 0.00884 0.00316 -0.0860 0.2563 1.0000
5.500 1.0668 0.00903 0.00331 -0.0860 0.2448 1.0000
5.750 1.0928 0.00931 0.00351 -0.0858 0.2263 1.0000
6.000 1.1158 0.00997 0.00388 -0.0852 0.1756 1.0000
6.250 1.1362 0.01097 0.00453 -0.0843 0.1142 1.0000
6.500 1.1595 0.01158 0.00499 -0.0838 0.0874 1.0000
6.750 1.1844 0.01197 0.00534 -0.0834 0.0759 1.0000
7.000 1.2087 0.01240 0.00571 -0.0830 0.0620 1.0000
7.250 1.2275 0.01353 0.00655 -0.0818 0.0166 1.0000
7.500 1.2519 0.01391 0.00696 -0.0814 0.0130 1.0000
7.750 1.2758 0.01434 0.00740 -0.0809 0.0109 1.0000
8.000 1.2998 0.01473 0.00782 -0.0804 0.0099 1.0000
8.250 1.3236 0.01511 0.00824 -0.0799 0.0091 1.0000
8.500 1.3468 0.01556 0.00871 -0.0794 0.0082 1.0000
8.750 1.3689 0.01610 0.00929 -0.0786 0.0072 1.0000
9.000 1.3915 0.01654 0.00977 -0.0780 0.0068 1.0000
9.250 1.4137 0.01701 0.01029 -0.0773 0.0064 1.0000
9.500 1.4352 0.01751 0.01083 -0.0765 0.0060 1.0000
9.750 1.4560 0.01806 0.01141 -0.0756 0.0056 1.0000
10.000 1.4756 0.01867 0.01208 -0.0745 0.0053 1.0000
10.250 1.4930 0.01946 0.01293 -0.0731 0.0049 1.0000
10.500 1.5119 0.02005 0.01358 -0.0720 0.0047 1.0000
10.750 1.5297 0.02068 0.01428 -0.0707 0.0045 1.0000
11.000 1.5464 0.02135 0.01500 -0.0693 0.0043 1.0000
11.250 1.5614 0.02205 0.01577 -0.0676 0.0041 1.0000
11.500 1.5728 0.02279 0.01657 -0.0653 0.0039 1.0000
11.750 1.5829 0.02363 0.01749 -0.0630 0.0038 1.0000
12.000 1.5921 0.02457 0.01849 -0.0607 0.0037 1.0000
12.250 1.5995 0.02568 0.01967 -0.0584 0.0035 1.0000
12.500 1.6044 0.02703 0.02111 -0.0560 0.0034 1.0000
12.750 1.6051 0.02881 0.02300 -0.0536 0.0033 1.0000
13.000 1.6090 0.03047 0.02475 -0.0518 0.0032 1.0000
13.250 1.6129 0.03226 0.02664 -0.0503 0.0032 1.0000
13.500 1.6150 0.03434 0.02883 -0.0490 0.0031 1.0000
13.750 1.6158 0.03674 0.03134 -0.0481 0.0031 1.0000
14.000 1.6154 0.03946 0.03418 -0.0476 0.0030 1.0000
14.250 1.6134 0.04255 0.03738 -0.0475 0.0030 1.0000
14.500 1.6092 0.04610 0.04106 -0.0476 0.0029 1.0000
14.750 1.6040 0.04989 0.04498 -0.0481 0.0029 1.0000
15.000 1.5960 0.05423 0.04944 -0.0488 0.0028 1.0000
15.250 1.5876 0.05876 0.05410 -0.0498 0.0028 1.0000
15.500 1.5769 0.06373 0.05920 -0.0510 0.0028 1.0000
15.750 1.5652 0.06897 0.06456 -0.0525 0.0027 1.0000
16.000 1.5515 0.07461 0.07032 -0.0541 0.0027 1.0000
16.250 1.5372 0.08038 0.07621 -0.0558 0.0027 1.0000
16.500 1.5226 0.08632 0.08227 -0.0576 0.0027 1.0000
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Polar data table (+)
Polar graphs
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