GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Reynolds number: 200,000 Max Cl/Cd: 72.1 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe278-il-200000-n5.txt Download as CSV file: xf-goe278-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3459 0.09444 0.09100 -0.0273 1.0000 0.0231
-7.750 -0.3544 0.09266 0.08931 -0.0262 1.0000 0.0232
-7.500 -0.3604 0.09059 0.08729 -0.0259 1.0000 0.0232
-7.250 -0.3637 0.08821 0.08496 -0.0264 0.9996 0.0232
-7.000 -0.3371 0.08292 0.07962 -0.0355 0.9948 0.0233
-6.750 -0.3104 0.07768 0.07432 -0.0434 0.9895 0.0233
-6.250 -0.2738 0.06936 0.06598 -0.0481 0.9817 0.0245
-6.000 -0.2467 0.06558 0.06216 -0.0532 0.9774 0.0261
-5.750 -0.2154 0.06118 0.05767 -0.0600 0.9720 0.0278
-5.500 -0.1657 0.05602 0.05218 -0.0712 0.9667 0.0296
-5.250 -0.1282 0.05161 0.04750 -0.0768 0.9634 0.0298
-5.000 -0.1125 0.04688 0.04280 -0.0785 0.9573 0.0308
-4.750 -0.0847 0.04393 0.03979 -0.0811 0.9530 0.0320
-4.500 -0.0547 0.04096 0.03667 -0.0837 0.9469 0.0337
-4.250 -0.0094 0.03929 0.03442 -0.0868 0.9402 0.0387
-4.000 0.0175 0.03425 0.02926 -0.0896 0.9351 0.0401
-3.750 0.0422 0.03195 0.02690 -0.0903 0.9266 0.0414
-3.500 0.0737 0.02973 0.02449 -0.0919 0.9205 0.0433
-3.250 0.1017 0.02779 0.02232 -0.0922 0.9103 0.0454
-2.750 0.1652 0.02288 0.01656 -0.0925 0.8917 0.0374
-2.500 0.1924 0.02122 0.01464 -0.0923 0.8819 0.0371
-2.000 0.2494 0.01896 0.01183 -0.0918 0.8634 0.0384
-1.750 0.2766 0.01767 0.01034 -0.0915 0.8526 0.0381
-1.500 0.3043 0.01664 0.00911 -0.0911 0.8416 0.0380
-1.250 0.3319 0.01580 0.00809 -0.0908 0.8298 0.0382
-1.000 0.3592 0.01522 0.00735 -0.0903 0.8161 0.0387
-0.750 0.3858 0.01425 0.00627 -0.0899 0.8002 0.0402
-0.500 0.4125 0.01367 0.00559 -0.0894 0.7809 0.0405
-0.250 0.4391 0.01317 0.00499 -0.0888 0.7585 0.0405
0.000 0.4654 0.01274 0.00446 -0.0882 0.7321 0.0408
0.250 0.4913 0.01242 0.00402 -0.0876 0.7031 0.0412
0.500 0.5169 0.01220 0.00366 -0.0869 0.6740 0.0419
0.750 0.5423 0.01208 0.00340 -0.0863 0.6472 0.0428
1.000 0.5677 0.01203 0.00322 -0.0857 0.6222 0.0439
1.250 0.5933 0.01205 0.00313 -0.0852 0.5984 0.0464
1.500 0.6188 0.01212 0.00307 -0.0846 0.5749 0.0488
1.750 0.6447 0.01219 0.00301 -0.0842 0.5514 0.0500
2.000 0.6703 0.01227 0.00298 -0.0837 0.5276 0.0525
2.250 0.6958 0.01239 0.00301 -0.0832 0.5027 0.0573
2.500 0.7210 0.01254 0.00310 -0.0827 0.4771 0.0761
3.000 0.7705 0.01126 0.00341 -0.0817 0.4304 1.0000
3.500 0.8209 0.01183 0.00376 -0.0807 0.4007 1.0000
3.750 0.8456 0.01215 0.00396 -0.0802 0.3835 1.0000
4.000 0.8699 0.01251 0.00419 -0.0796 0.3644 1.0000
4.250 0.8944 0.01284 0.00441 -0.0791 0.3474 1.0000
4.500 0.9196 0.01312 0.00465 -0.0787 0.3351 1.0000
4.750 0.9449 0.01339 0.00493 -0.0783 0.3264 1.0000
5.000 0.9699 0.01368 0.00520 -0.0778 0.3169 1.0000
5.250 0.9950 0.01396 0.00548 -0.0774 0.3046 1.0000
5.500 1.0200 0.01424 0.00578 -0.0770 0.2939 1.0000
5.750 1.0447 0.01454 0.00610 -0.0765 0.2821 1.0000
6.000 1.0693 0.01483 0.00642 -0.0760 0.2671 1.0000
6.250 1.0930 0.01520 0.00674 -0.0755 0.2418 1.0000
6.500 1.1154 0.01571 0.00713 -0.0747 0.2034 1.0000
6.750 1.1336 0.01671 0.00779 -0.0735 0.1507 1.0000
7.000 1.1467 0.01838 0.00889 -0.0718 0.0661 1.0000
7.250 1.1664 0.01922 0.00970 -0.0706 0.0556 1.0000
7.500 1.1877 0.01985 0.01041 -0.0697 0.0520 1.0000
7.750 1.2085 0.02050 0.01119 -0.0687 0.0496 1.0000
8.000 1.2281 0.02125 0.01203 -0.0676 0.0472 1.0000
8.250 1.2457 0.02214 0.01302 -0.0662 0.0447 1.0000
8.500 1.2620 0.02309 0.01408 -0.0646 0.0428 1.0000
8.750 1.2796 0.02387 0.01502 -0.0633 0.0414 1.0000
9.000 1.2957 0.02473 0.01601 -0.0617 0.0395 1.0000
9.250 1.3100 0.02569 0.01708 -0.0600 0.0376 1.0000
9.500 1.3221 0.02676 0.01824 -0.0580 0.0358 1.0000
9.750 1.3281 0.02808 0.01963 -0.0551 0.0340 1.0000
10.000 1.3306 0.02976 0.02137 -0.0520 0.0324 1.0000
10.250 1.3429 0.03069 0.02248 -0.0502 0.0311 1.0000
10.500 1.3527 0.03185 0.02379 -0.0482 0.0294 1.0000
10.750 1.3605 0.03319 0.02525 -0.0462 0.0279 1.0000
11.000 1.3673 0.03464 0.02680 -0.0443 0.0264 1.0000
11.250 1.3714 0.03636 0.02859 -0.0425 0.0250 1.0000
11.500 1.3724 0.03854 0.03085 -0.0405 0.0238 1.0000
11.750 1.3797 0.04015 0.03268 -0.0391 0.0226 1.0000
12.000 1.3845 0.04209 0.03479 -0.0377 0.0214 1.0000
12.250 1.3883 0.04413 0.03698 -0.0366 0.0202 1.0000
12.500 1.3916 0.04627 0.03923 -0.0358 0.0192 1.0000
12.750 1.3937 0.04860 0.04166 -0.0353 0.0184 1.0000
13.000 1.3923 0.05145 0.04458 -0.0348 0.0177 1.0000
13.250 1.3930 0.05429 0.04765 -0.0344 0.0169 1.0000
13.500 1.3918 0.05743 0.05098 -0.0340 0.0162 1.0000
13.750 1.3895 0.06079 0.05451 -0.0341 0.0156 1.0000
14.000 1.3866 0.06434 0.05825 -0.0344 0.0151 1.0000
14.250 1.3830 0.06807 0.06213 -0.0351 0.0147 1.0000
14.500 1.3787 0.07199 0.06619 -0.0361 0.0143 1.0000
14.750 1.3738 0.07614 0.07047 -0.0374 0.0140 1.0000
15.000 1.3683 0.08053 0.07498 -0.0390 0.0137 1.0000
15.250 1.3612 0.08523 0.07980 -0.0407 0.0134 1.0000
15.500 1.3527 0.09024 0.08493 -0.0424 0.0131 1.0000
15.750 1.3425 0.09581 0.09072 -0.0445 0.0128 1.0000
16.000 1.3311 0.10172 0.09685 -0.0468 0.0126 1.0000
16.250 1.3186 0.10798 0.10333 -0.0496 0.0123 1.0000
16.500 1.3054 0.11461 0.11016 -0.0528 0.0121 1.0000
16.750 1.2914 0.12163 0.11736 -0.0563 0.0120 1.0000
17.000 1.2762 0.12913 0.12506 -0.0603 0.0119 1.0000
17.250 1.2597 0.13720 0.13330 -0.0649 0.0118 1.0000
17.500 1.2413 0.14616 0.14244 -0.0702 0.0118 1.0000
17.750 1.2203 0.15638 0.15284 -0.0765 0.0119 1.0000
18.000 1.1943 0.16884 0.16547 -0.0842 0.0121 1.0000
18.250 1.1565 0.18684 0.18359 -0.0952 0.0127 1.0000
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