GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Reynolds number: 500,000 Max Cl/Cd: 95.86 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe278-il-500000.txt Download as CSV file: xf-goe278-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 278 (DAIMLER IX) 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 -0.3635 0.09112 0.08892 -0.0261 1.0000 0.0186
-7.750 -0.3736 0.08927 0.08713 -0.0256 1.0000 0.0186
-7.500 -0.3853 0.08763 0.08554 -0.0243 1.0000 0.0186
-7.250 -0.3733 0.08344 0.08134 -0.0301 0.9982 0.0187
-7.000 -0.3504 0.07738 0.07525 -0.0370 0.9955 0.0188
-6.750 -0.3335 0.07370 0.07158 -0.0376 0.9939 0.0191
-6.500 -0.3096 0.06985 0.06770 -0.0421 0.9903 0.0195
-6.250 -0.2794 0.06555 0.06336 -0.0488 0.9870 0.0201
-6.000 -0.2442 0.06080 0.05854 -0.0567 0.9845 0.0212
-5.750 -0.1901 0.05450 0.05195 -0.0698 0.9788 0.0230
-5.500 -0.1581 0.04834 0.04563 -0.0756 0.9755 0.0232
-5.250 -0.1322 0.04486 0.04214 -0.0787 0.9734 0.0237
-5.000 -0.1011 0.04194 0.03915 -0.0821 0.9711 0.0243
-4.750 -0.0747 0.03922 0.03633 -0.0840 0.9643 0.0253
-4.500 -0.0300 0.03645 0.03314 -0.0870 0.9598 0.0284
-4.250 -0.0031 0.03165 0.02805 -0.0887 0.9533 0.0289
-4.000 0.0199 0.02912 0.02549 -0.0895 0.9458 0.0295
-3.750 0.0442 0.02736 0.02365 -0.0897 0.9379 0.0303
-3.500 0.0698 0.02569 0.02184 -0.0898 0.9306 0.0316
-3.250 0.1019 0.02545 0.02126 -0.0890 0.9237 0.0355
-3.000 0.1261 0.02169 0.01718 -0.0890 0.9164 0.0366
-2.750 0.1507 0.02019 0.01563 -0.0891 0.9091 0.0376
-2.500 0.1761 0.01908 0.01442 -0.0888 0.9009 0.0391
-2.250 0.2027 0.01811 0.01330 -0.0884 0.8924 0.0417
-2.000 0.2306 0.01693 0.01174 -0.0877 0.8837 0.0465
-1.750 0.2560 0.01580 0.01060 -0.0875 0.8732 0.0483
-1.500 0.2825 0.01507 0.00977 -0.0871 0.8632 0.0513
-1.250 0.3101 0.01449 0.00889 -0.0865 0.8526 0.0586
-1.000 0.3361 0.01351 0.00793 -0.0863 0.8399 0.0615
-0.750 0.3632 0.01328 0.00758 -0.0859 0.8258 0.0677
-0.500 0.3895 0.01236 0.00657 -0.0856 0.8099 0.0755
0.000 0.4454 0.01049 0.00421 -0.0835 0.7676 0.0458
0.250 0.4713 0.01011 0.00371 -0.0828 0.7359 0.0445
0.500 0.4964 0.00971 0.00314 -0.0820 0.6986 0.0441
0.750 0.5215 0.00954 0.00280 -0.0813 0.6635 0.0441
1.000 0.5469 0.00957 0.00268 -0.0807 0.6330 0.0449
1.250 0.5725 0.00949 0.00247 -0.0802 0.6050 0.0450
1.500 0.5982 0.00940 0.00226 -0.0797 0.5762 0.0454
1.750 0.6240 0.00935 0.00208 -0.0793 0.5454 0.0468
2.000 0.6498 0.00943 0.00203 -0.0788 0.5106 0.0492
2.250 0.6749 0.00964 0.00204 -0.0783 0.4688 0.0524
2.750 0.7249 0.00816 0.00234 -0.0777 0.4093 1.0000
3.000 0.7509 0.00840 0.00244 -0.0774 0.3930 1.0000
3.250 0.7768 0.00864 0.00257 -0.0770 0.3772 1.0000
3.500 0.8029 0.00886 0.00270 -0.0767 0.3634 1.0000
3.750 0.8290 0.00908 0.00285 -0.0764 0.3525 1.0000
4.000 0.8551 0.00929 0.00302 -0.0761 0.3429 1.0000
4.250 0.8816 0.00946 0.00317 -0.0759 0.3341 1.0000
4.500 0.9076 0.00969 0.00335 -0.0756 0.3247 1.0000
4.750 0.9336 0.00990 0.00353 -0.0753 0.3124 1.0000
5.000 0.9599 0.01007 0.00370 -0.0751 0.3009 1.0000
5.250 0.9859 0.01029 0.00389 -0.0748 0.2864 1.0000
5.500 1.0113 0.01055 0.00407 -0.0745 0.2630 1.0000
5.750 1.0340 0.01115 0.00436 -0.0738 0.2003 1.0000
6.000 1.0476 0.01293 0.00535 -0.0720 0.0713 1.0000
6.250 1.0699 0.01364 0.00596 -0.0711 0.0516 1.0000
6.500 1.0935 0.01415 0.00648 -0.0705 0.0472 1.0000
6.750 1.1163 0.01475 0.00714 -0.0697 0.0436 1.0000
7.000 1.1396 0.01526 0.00771 -0.0690 0.0423 1.0000
7.250 1.1628 0.01575 0.00827 -0.0683 0.0407 1.0000
7.500 1.1850 0.01633 0.00891 -0.0675 0.0390 1.0000
7.750 1.2063 0.01698 0.00963 -0.0666 0.0373 1.0000
8.000 1.2252 0.01786 0.01056 -0.0653 0.0353 1.0000
8.250 1.2385 0.01929 0.01210 -0.0632 0.0333 1.0000
8.500 1.2601 0.01980 0.01268 -0.0623 0.0325 1.0000
8.750 1.2801 0.02043 0.01339 -0.0612 0.0312 1.0000
9.000 1.2991 0.02114 0.01417 -0.0600 0.0296 1.0000
9.250 1.3163 0.02197 0.01504 -0.0586 0.0282 1.0000
9.500 1.3295 0.02315 0.01625 -0.0567 0.0269 1.0000
9.750 1.3352 0.02525 0.01844 -0.0537 0.0254 1.0000
10.000 1.3541 0.02563 0.01893 -0.0525 0.0245 1.0000
10.250 1.3684 0.02634 0.01973 -0.0507 0.0233 1.0000
10.500 1.3806 0.02721 0.02067 -0.0486 0.0223 1.0000
10.750 1.3919 0.02814 0.02166 -0.0466 0.0214 1.0000
11.000 1.4010 0.02928 0.02283 -0.0445 0.0206 1.0000
11.250 1.4024 0.03197 0.02559 -0.0416 0.0196 1.0000
11.500 1.4129 0.03275 0.02652 -0.0398 0.0191 1.0000
11.750 1.4221 0.03386 0.02776 -0.0381 0.0183 1.0000
12.000 1.4301 0.03516 0.02917 -0.0364 0.0175 1.0000
12.250 1.4369 0.03662 0.03073 -0.0349 0.0169 1.0000
12.500 1.4430 0.03815 0.03235 -0.0335 0.0164 1.0000
12.750 1.4481 0.03984 0.03413 -0.0323 0.0160 1.0000
13.000 1.4509 0.04192 0.03627 -0.0311 0.0156 1.0000
13.250 1.4455 0.04547 0.03995 -0.0291 0.0150 1.0000
13.500 1.4466 0.04785 0.04251 -0.0283 0.0148 1.0000
13.750 1.4458 0.05062 0.04546 -0.0277 0.0145 1.0000
14.000 1.4434 0.05370 0.04873 -0.0273 0.0141 1.0000
14.250 1.4397 0.05707 0.05226 -0.0272 0.0138 1.0000
14.500 1.4350 0.06069 0.05605 -0.0275 0.0135 1.0000
14.750 1.4306 0.06439 0.05989 -0.0283 0.0132 1.0000
15.000 1.4242 0.06849 0.06414 -0.0294 0.0130 1.0000
15.250 1.4173 0.07284 0.06862 -0.0309 0.0127 1.0000
15.500 1.4110 0.07728 0.07320 -0.0327 0.0125 1.0000
15.750 1.4038 0.08202 0.07805 -0.0346 0.0124 1.0000
16.000 1.3947 0.08717 0.08333 -0.0368 0.0122 1.0000
16.250 1.3857 0.09247 0.08874 -0.0392 0.0121 1.0000
16.500 1.3741 0.09837 0.09478 -0.0419 0.0120 1.0000
16.750 1.3612 0.10462 0.10117 -0.0449 0.0119 1.0000
17.000 1.3462 0.11144 0.10813 -0.0482 0.0118 1.0000
17.250 1.3296 0.11883 0.11568 -0.0521 0.0118 1.0000
17.500 1.3111 0.12692 0.12393 -0.0565 0.0118 1.0000
17.750 1.2909 0.13568 0.13286 -0.0616 0.0118 1.0000
18.000 1.2649 0.14641 0.14381 -0.0681 0.0119 1.0000
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