GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Reynolds number: 200,000 Max Cl/Cd: 77.41 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe279-il-200000.txt Download as CSV file: xf-goe279-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3470 0.09971 0.09621 -0.0273 1.0000 0.0280
-8.000 -0.3568 0.09842 0.09501 -0.0265 1.0000 0.0281
-7.750 -0.3636 0.09675 0.09342 -0.0271 1.0000 0.0282
-7.500 -0.3681 0.09486 0.09157 -0.0280 1.0000 0.0282
-7.250 -0.3703 0.09272 0.08946 -0.0291 1.0000 0.0283
-7.000 -0.3697 0.09031 0.08705 -0.0304 1.0000 0.0283
-6.750 -0.3711 0.08632 0.08312 -0.0284 1.0000 0.0285
-6.500 -0.3726 0.08294 0.07979 -0.0244 1.0000 0.0289
-6.250 -0.3717 0.08016 0.07704 -0.0225 1.0000 0.0292
-6.000 -0.3687 0.07746 0.07435 -0.0219 1.0000 0.0296
-5.750 -0.3632 0.07468 0.07157 -0.0223 1.0000 0.0302
-5.500 -0.3548 0.07177 0.06864 -0.0233 1.0000 0.0308
-5.250 -0.3342 0.06813 0.06496 -0.0272 0.9987 0.0321
-5.000 -0.2623 0.06371 0.06010 -0.0434 0.9944 0.0354
-4.750 -0.2320 0.05789 0.05416 -0.0484 0.9908 0.0359
-4.500 -0.2105 0.05351 0.04985 -0.0505 0.9875 0.0368
-4.250 -0.1775 0.04992 0.04618 -0.0546 0.9846 0.0383
-4.000 -0.1425 0.04654 0.04266 -0.0586 0.9803 0.0406
-3.750 -0.0819 0.04509 0.04045 -0.0648 0.9756 0.0448
-3.500 -0.0552 0.03896 0.03452 -0.0687 0.9731 0.0469
-3.250 -0.0180 0.03629 0.03173 -0.0721 0.9687 0.0508
-3.000 0.0301 0.03358 0.02844 -0.0758 0.9629 0.0570
-2.750 0.0715 0.03038 0.02526 -0.0803 0.9593 0.0610
-2.500 0.1142 0.02811 0.02263 -0.0834 0.9540 0.0715
-2.250 0.1554 0.02625 0.02048 -0.0863 0.9480 0.0850
-2.000 0.2018 0.02399 0.01811 -0.0907 0.9446 0.1011
-1.000 -0.3126 0.05859 0.05572 0.0014 0.8952 0.0520
-0.750 0.4026 0.01687 0.00963 -0.0983 0.9161 0.0821
-0.500 0.4347 0.01534 0.00807 -0.0985 0.9077 0.0765
-0.250 0.4681 0.01447 0.00712 -0.0988 0.8997 0.0764
0.000 0.4962 0.01379 0.00643 -0.0981 0.8879 0.0762
0.250 0.5246 0.01315 0.00579 -0.0975 0.8757 0.0758
0.500 0.5524 0.01261 0.00526 -0.0968 0.8622 0.0768
0.750 0.5797 0.01218 0.00484 -0.0961 0.8469 0.0796
1.000 0.6067 0.01185 0.00449 -0.0954 0.8297 0.0833
1.250 0.6338 0.01149 0.00409 -0.0946 0.8099 0.0880
1.500 0.6600 0.01131 0.00384 -0.0937 0.7843 0.0957
1.750 0.6824 0.00985 0.00378 -0.0927 0.7561 0.6812
2.000 0.7057 0.00929 0.00352 -0.0905 0.7214 1.0000
2.250 0.7309 0.00945 0.00338 -0.0894 0.6801 1.0000
2.500 0.7555 0.00976 0.00336 -0.0884 0.6410 1.0000
2.750 0.7800 0.01013 0.00347 -0.0875 0.6058 1.0000
3.000 0.8045 0.01052 0.00364 -0.0868 0.5730 1.0000
3.250 0.8287 0.01091 0.00382 -0.0860 0.5391 1.0000
3.500 0.8529 0.01128 0.00401 -0.0852 0.5047 1.0000
3.750 0.8771 0.01166 0.00424 -0.0845 0.4735 1.0000
4.000 0.9013 0.01205 0.00447 -0.0839 0.4467 1.0000
4.250 0.9261 0.01242 0.00473 -0.0833 0.4243 1.0000
4.500 0.9505 0.01283 0.00501 -0.0827 0.4046 1.0000
4.750 0.9751 0.01322 0.00532 -0.0822 0.3865 1.0000
5.000 0.9997 0.01361 0.00564 -0.0817 0.3700 1.0000
5.250 1.0243 0.01401 0.00599 -0.0812 0.3556 1.0000
5.500 1.0488 0.01442 0.00635 -0.0807 0.3417 1.0000
5.750 1.0731 0.01482 0.00673 -0.0802 0.3276 1.0000
6.000 1.0971 0.01521 0.00710 -0.0796 0.3129 1.0000
6.250 1.1214 0.01557 0.00749 -0.0791 0.2991 1.0000
6.500 1.1455 0.01592 0.00789 -0.0785 0.2852 1.0000
6.750 1.1693 0.01628 0.00830 -0.0779 0.2703 1.0000
7.000 1.1926 0.01666 0.00870 -0.0773 0.2545 1.0000
7.250 1.2159 0.01702 0.00909 -0.0766 0.2356 1.0000
7.500 1.2387 0.01742 0.00953 -0.0759 0.2162 1.0000
7.750 1.2606 0.01792 0.01001 -0.0751 0.1975 1.0000
8.000 1.2823 0.01845 0.01053 -0.0742 0.1768 1.0000
8.500 1.3204 0.02004 0.01197 -0.0719 0.1294 1.0000
8.750 1.3361 0.02120 0.01300 -0.0703 0.1012 1.0000
9.000 1.3530 0.02223 0.01395 -0.0687 0.0776 1.0000
9.250 1.3681 0.02334 0.01499 -0.0669 0.0671 1.0000
9.500 1.3823 0.02444 0.01615 -0.0650 0.0616 1.0000
9.750 1.3935 0.02572 0.01748 -0.0627 0.0574 1.0000
10.000 1.4019 0.02714 0.01897 -0.0600 0.0543 1.0000
10.250 1.4103 0.02836 0.02033 -0.0573 0.0517 1.0000
10.500 1.4164 0.02980 0.02186 -0.0544 0.0491 1.0000
10.750 1.4182 0.03171 0.02379 -0.0513 0.0467 1.0000
11.000 1.4225 0.03373 0.02591 -0.0485 0.0447 1.0000
11.250 1.4302 0.03536 0.02773 -0.0463 0.0429 1.0000
11.500 1.4365 0.03717 0.02967 -0.0441 0.0408 1.0000
11.750 1.4418 0.03918 0.03174 -0.0421 0.0387 1.0000
12.000 1.4535 0.04299 0.03555 -0.0406 0.0361 1.0000
12.250 1.4558 0.04480 0.03761 -0.0383 0.0353 1.0000
12.500 1.4577 0.04700 0.04007 -0.0363 0.0342 1.0000
12.750 1.4582 0.04945 0.04274 -0.0345 0.0329 1.0000
13.000 1.4589 0.05199 0.04545 -0.0330 0.0316 1.0000
13.250 1.4576 0.05473 0.04835 -0.0316 0.0304 1.0000
13.500 1.4573 0.05778 0.05150 -0.0305 0.0294 1.0000
13.750 1.4559 0.06186 0.05573 -0.0293 0.0285 1.0000
14.000 1.4444 0.06729 0.06143 -0.0283 0.0280 1.0000
14.250 1.4270 0.07245 0.06686 -0.0279 0.0278 1.0000
14.500 1.4104 0.07694 0.07160 -0.0284 0.0277 1.0000
14.750 1.3930 0.08204 0.07694 -0.0296 0.0276 1.0000
15.000 1.3744 0.08772 0.08285 -0.0316 0.0276 1.0000
15.250 1.3549 0.09398 0.08934 -0.0343 0.0276 1.0000
15.500 1.3347 0.10080 0.09636 -0.0377 0.0276 1.0000
15.750 1.3138 0.10826 0.10402 -0.0417 0.0277 1.0000
16.000 1.2923 0.11639 0.11234 -0.0463 0.0278 1.0000
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Polar data table (+)
Polar graphs
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