GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Reynolds number: 100,000 Max Cl/Cd: 59.05 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe279-il-100000-n5.txt Download as CSV file: xf-goe279-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.3400 0.11021 0.10538 -0.0305 1.0000 0.0308
-8.250 -0.3459 0.10849 0.10375 -0.0296 1.0000 0.0308
-8.000 -0.3486 0.10640 0.10173 -0.0297 1.0000 0.0308
-7.750 -0.3506 0.10423 0.09962 -0.0300 1.0000 0.0309
-7.500 -0.3516 0.10199 0.09743 -0.0305 1.0000 0.0309
-7.250 -0.3505 0.09654 0.09205 -0.0255 1.0000 0.0315
-7.000 -0.3492 0.09320 0.08876 -0.0221 1.0000 0.0323
-6.750 -0.3505 0.09081 0.08641 -0.0208 1.0000 0.0330
-6.500 -0.3513 0.08847 0.08412 -0.0203 1.0000 0.0337
-6.250 -0.3506 0.08604 0.08173 -0.0203 1.0000 0.0344
-6.000 -0.3283 0.08197 0.07762 -0.0259 0.9961 0.0357
-5.750 -0.2968 0.07733 0.07291 -0.0337 0.9902 0.0373
-5.500 -0.2592 0.07273 0.06821 -0.0432 0.9846 0.0394
-5.250 -0.2092 0.06854 0.06374 -0.0556 0.9786 0.0407
-5.000 -0.1710 0.06451 0.05947 -0.0625 0.9736 0.0410
-4.750 -0.1472 0.05926 0.05419 -0.0656 0.9691 0.0416
-4.500 -0.1295 0.05542 0.05044 -0.0664 0.9659 0.0441
-4.250 -0.0996 0.05219 0.04708 -0.0699 0.9603 0.0480
-4.000 -0.0417 0.04961 0.04380 -0.0780 0.9553 0.0523
-3.750 -0.0138 0.04441 0.03867 -0.0812 0.9525 0.0537
-3.500 0.0115 0.04152 0.03572 -0.0826 0.9462 0.0560
-3.000 0.0994 0.03565 0.02881 -0.0894 0.9386 0.0520
-2.750 0.1287 0.03204 0.02516 -0.0912 0.9333 0.0465
-2.500 0.1657 0.02986 0.02259 -0.0931 0.9280 0.0492
-2.250 0.2076 0.02743 0.01973 -0.0957 0.9244 0.0483
-2.000 0.2450 0.02566 0.01752 -0.0972 0.9180 0.0499
-1.750 0.2841 0.02424 0.01561 -0.0986 0.9108 0.0518
-1.500 0.3209 0.02283 0.01385 -0.0997 0.9023 0.0522
-1.250 0.3584 0.02116 0.01213 -0.1015 0.8935 0.0561
-1.000 0.3900 0.02015 0.01096 -0.1016 0.8819 0.0576
-0.750 0.4220 0.01923 0.00990 -0.1018 0.8714 0.0583
-0.500 0.4560 0.01839 0.00896 -0.1025 0.8629 0.0594
-0.250 0.4840 0.01788 0.00839 -0.1020 0.8506 0.0628
0.000 0.5125 0.01731 0.00780 -0.1017 0.8382 0.0648
0.250 0.5406 0.01670 0.00722 -0.1014 0.8250 0.0661
0.500 0.5688 0.01627 0.00676 -0.1010 0.8104 0.0680
0.750 0.5970 0.01595 0.00638 -0.1006 0.7942 0.0705
1.000 0.6255 0.01571 0.00604 -0.1003 0.7763 0.0739
1.250 0.6534 0.01550 0.00577 -0.0999 0.7559 0.0820
1.500 0.6810 0.01532 0.00556 -0.0994 0.7320 0.0960
1.750 0.7035 0.01332 0.00544 -0.0979 0.7073 1.0000
2.000 0.7316 0.01338 0.00521 -0.0973 0.6797 1.0000
2.250 0.7593 0.01351 0.00507 -0.0968 0.6523 1.0000
2.500 0.7860 0.01373 0.00504 -0.0962 0.6256 1.0000
2.750 0.8120 0.01402 0.00511 -0.0956 0.5993 1.0000
3.000 0.8374 0.01435 0.00526 -0.0949 0.5732 1.0000
3.250 0.8623 0.01470 0.00544 -0.0942 0.5467 1.0000
3.500 0.8866 0.01507 0.00566 -0.0935 0.5186 1.0000
3.750 0.9107 0.01544 0.00591 -0.0927 0.4907 1.0000
4.000 0.9347 0.01583 0.00616 -0.0920 0.4645 1.0000
4.500 0.9823 0.01667 0.00678 -0.0905 0.4183 1.0000
4.750 1.0060 0.01711 0.00712 -0.0898 0.3987 1.0000
5.000 1.0296 0.01757 0.00750 -0.0891 0.3820 1.0000
5.250 1.0535 0.01803 0.00792 -0.0885 0.3678 1.0000
5.500 1.0773 0.01849 0.00839 -0.0879 0.3547 1.0000
5.750 1.1010 0.01897 0.00887 -0.0873 0.3423 1.0000
6.000 1.1242 0.01946 0.00937 -0.0866 0.3297 1.0000
6.250 1.1470 0.01998 0.00992 -0.0859 0.3161 1.0000
6.500 1.1692 0.02049 0.01045 -0.0850 0.3012 1.0000
6.750 1.1910 0.02100 0.01099 -0.0842 0.2846 1.0000
7.000 1.2125 0.02151 0.01154 -0.0833 0.2679 1.0000
7.250 1.2341 0.02203 0.01216 -0.0824 0.2537 1.0000
7.500 1.2555 0.02257 0.01278 -0.0815 0.2416 1.0000
7.750 1.2765 0.02314 0.01343 -0.0806 0.2293 1.0000
8.000 1.2970 0.02372 0.01412 -0.0796 0.2156 1.0000
8.250 1.3164 0.02437 0.01485 -0.0784 0.2004 1.0000
8.500 1.3353 0.02505 0.01561 -0.0772 0.1864 1.0000
8.750 1.3537 0.02579 0.01644 -0.0760 0.1737 1.0000
9.000 1.3704 0.02661 0.01732 -0.0745 0.1598 1.0000
9.250 1.3857 0.02753 0.01829 -0.0729 0.1462 1.0000
9.500 1.3996 0.02856 0.01941 -0.0712 0.1329 1.0000
9.750 1.4117 0.02970 0.02061 -0.0692 0.1192 1.0000
10.000 1.4221 0.03089 0.02191 -0.0670 0.1058 1.0000
10.250 1.4307 0.03212 0.02328 -0.0645 0.0929 1.0000
10.500 1.4379 0.03349 0.02475 -0.0620 0.0806 1.0000
10.750 1.4429 0.03502 0.02633 -0.0594 0.0717 1.0000
11.000 1.4453 0.03679 0.02810 -0.0569 0.0652 1.0000
11.250 1.4471 0.03866 0.03012 -0.0545 0.0601 1.0000
11.500 1.4445 0.04095 0.03245 -0.0521 0.0562 1.0000
11.750 1.4437 0.04322 0.03489 -0.0500 0.0528 1.0000
12.000 1.4409 0.04578 0.03762 -0.0482 0.0497 1.0000
12.250 1.4344 0.04882 0.04078 -0.0467 0.0472 1.0000
12.500 1.4245 0.05237 0.04439 -0.0454 0.0452 1.0000
12.750 1.4211 0.05551 0.04779 -0.0446 0.0431 1.0000
13.000 1.4150 0.05909 0.05159 -0.0442 0.0410 1.0000
13.250 1.4071 0.06307 0.05574 -0.0442 0.0392 1.0000
13.500 1.3976 0.06745 0.06027 -0.0446 0.0376 1.0000
13.750 1.3866 0.07212 0.06504 -0.0452 0.0362 1.0000
14.000 1.3772 0.07662 0.06961 -0.0456 0.0346 1.0000
14.250 1.3691 0.08141 0.07467 -0.0468 0.0334 1.0000
14.500 1.3603 0.08640 0.07990 -0.0482 0.0321 1.0000
14.750 1.3510 0.09161 0.08530 -0.0498 0.0309 1.0000
15.000 1.3412 0.09703 0.09090 -0.0517 0.0298 1.0000
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Polar data table (+)
Polar graphs
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