GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Reynolds number: 500,000 Max Cl/Cd: 96.88 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe279-il-500000.txt Download as CSV file: xf-goe279-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 279 (DAIMLER X) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3446 0.09219 0.08999 -0.0244 1.0000 0.0158
-7.750 -0.3554 0.09088 0.08874 -0.0215 1.0000 0.0160
-7.500 -0.3763 0.09043 0.08837 -0.0165 1.0000 0.0161
-7.250 -0.3568 0.08624 0.08417 -0.0223 0.9972 0.0167
-7.000 -0.3314 0.08148 0.07940 -0.0302 0.9945 0.0174
-6.750 -0.2984 0.07606 0.07394 -0.0418 0.9897 0.0182
-6.500 -0.2559 0.06966 0.06744 -0.0563 0.9860 0.0184
-6.250 -0.2219 0.06364 0.06133 -0.0649 0.9841 0.0185
-6.000 -0.2080 0.06017 0.05788 -0.0653 0.9800 0.0188
-5.750 -0.1822 0.05677 0.05445 -0.0689 0.9770 0.0193
-5.500 -0.1494 0.05297 0.05057 -0.0744 0.9748 0.0201
-5.250 -0.1097 0.04859 0.04608 -0.0812 0.9730 0.0217
-5.000 -0.0545 0.04340 0.04049 -0.0893 0.9698 0.0228
-4.750 -0.0329 0.03873 0.03576 -0.0917 0.9638 0.0233
-4.500 -0.0044 0.03612 0.03310 -0.0940 0.9598 0.0239
-4.250 0.0244 0.03364 0.03051 -0.0957 0.9550 0.0248
-0.750 0.1541 0.00265 0.00022 -0.0531 0.8601 0.0475
-0.500 0.4442 0.01089 0.00493 -0.0947 0.8305 0.0522
-0.250 0.4719 0.01010 0.00396 -0.0940 0.8158 0.0465
0.000 0.4988 0.00971 0.00349 -0.0935 0.7967 0.0463
0.250 0.5254 0.00931 0.00305 -0.0930 0.7736 0.0475
0.500 0.5520 0.00907 0.00273 -0.0926 0.7448 0.0488
0.750 0.5780 0.00894 0.00245 -0.0920 0.7040 0.0497
1.000 0.6030 0.00900 0.00227 -0.0913 0.6564 0.0509
1.250 0.6284 0.00913 0.00219 -0.0907 0.6175 0.0524
1.500 0.6544 0.00926 0.00216 -0.0903 0.5867 0.0547
1.750 0.6810 0.00931 0.00211 -0.0900 0.5614 0.0574
2.000 0.7077 0.00939 0.00208 -0.0898 0.5370 0.0625
2.250 0.7343 0.00950 0.00210 -0.0895 0.5100 0.0723
2.500 0.7537 0.00778 0.00230 -0.0881 0.4820 1.0000
2.750 0.7794 0.00809 0.00240 -0.0877 0.4459 1.0000
3.000 0.8051 0.00841 0.00252 -0.0873 0.4123 1.0000
3.250 0.8306 0.00874 0.00268 -0.0869 0.3821 1.0000
3.500 0.8560 0.00909 0.00285 -0.0866 0.3572 1.0000
3.750 0.8821 0.00937 0.00304 -0.0863 0.3398 1.0000
4.000 0.9083 0.00963 0.00322 -0.0861 0.3261 1.0000
4.250 0.9346 0.00987 0.00341 -0.0859 0.3147 1.0000
4.500 0.9611 0.01008 0.00359 -0.0857 0.3047 1.0000
4.750 0.9873 0.01031 0.00380 -0.0854 0.2949 1.0000
5.000 1.0135 0.01055 0.00401 -0.0852 0.2845 1.0000
5.250 1.0398 0.01076 0.00420 -0.0850 0.2728 1.0000
5.500 1.0658 0.01101 0.00443 -0.0848 0.2592 1.0000
5.750 1.0916 0.01127 0.00465 -0.0845 0.2447 1.0000
6.000 1.1168 0.01157 0.00489 -0.0842 0.2267 1.0000
6.250 1.1416 0.01193 0.00516 -0.0838 0.2039 1.0000
6.500 1.1655 0.01239 0.00550 -0.0833 0.1765 1.0000
6.750 1.1886 0.01293 0.00591 -0.0827 0.1511 1.0000
7.000 1.2116 0.01349 0.00635 -0.0820 0.1319 1.0000
7.250 1.2349 0.01399 0.00680 -0.0814 0.1182 1.0000
7.500 1.2575 0.01455 0.00731 -0.0807 0.1016 1.0000
7.750 1.2775 0.01542 0.00791 -0.0797 0.0598 1.0000
8.000 1.2980 0.01621 0.00862 -0.0786 0.0487 1.0000
8.250 1.3198 0.01681 0.00927 -0.0778 0.0447 1.0000
8.500 1.3416 0.01739 0.00994 -0.0769 0.0426 1.0000
8.750 1.3619 0.01809 0.01070 -0.0758 0.0403 1.0000
9.000 1.3803 0.01895 0.01162 -0.0745 0.0380 1.0000
9.250 1.3965 0.01995 0.01273 -0.0728 0.0359 1.0000
9.500 1.4161 0.02058 0.01346 -0.0716 0.0349 1.0000
9.750 1.4339 0.02132 0.01429 -0.0702 0.0333 1.0000
10.000 1.4500 0.02216 0.01521 -0.0686 0.0316 1.0000
10.250 1.4625 0.02323 0.01635 -0.0665 0.0299 1.0000
10.500 1.4621 0.02505 0.01829 -0.0624 0.0282 1.0000
10.750 1.4745 0.02585 0.01920 -0.0603 0.0272 1.0000
11.000 1.4884 0.02656 0.02001 -0.0584 0.0258 1.0000
11.250 1.4999 0.02744 0.02097 -0.0564 0.0243 1.0000
11.500 1.5090 0.02851 0.02210 -0.0543 0.0231 1.0000
11.750 1.5097 0.03027 0.02394 -0.0514 0.0220 1.0000
12.000 1.5067 0.03249 0.02628 -0.0483 0.0210 1.0000
12.250 1.5187 0.03348 0.02741 -0.0470 0.0201 1.0000
12.500 1.5273 0.03480 0.02884 -0.0455 0.0191 1.0000
12.750 1.5357 0.03617 0.03029 -0.0442 0.0181 1.0000
13.000 1.5428 0.03772 0.03190 -0.0431 0.0173 1.0000
13.250 1.5391 0.04040 0.03466 -0.0415 0.0166 1.0000
13.500 1.5339 0.04342 0.03782 -0.0402 0.0160 1.0000
13.750 1.5369 0.04575 0.04030 -0.0395 0.0155 1.0000
14.000 1.5367 0.04853 0.04324 -0.0391 0.0150 1.0000
14.250 1.5354 0.05162 0.04646 -0.0390 0.0145 1.0000
14.500 1.5334 0.05496 0.04991 -0.0393 0.0140 1.0000
14.750 1.5305 0.05859 0.05367 -0.0399 0.0137 1.0000
15.000 1.5261 0.06260 0.05778 -0.0409 0.0134 1.0000
15.250 1.5192 0.06709 0.06238 -0.0422 0.0131 1.0000
15.500 1.5089 0.07213 0.06753 -0.0437 0.0128 1.0000
15.750 1.4948 0.07774 0.07327 -0.0452 0.0126 1.0000
16.000 1.4775 0.08383 0.07949 -0.0467 0.0124 1.0000
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Polar data table (+)
Polar graphs
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