GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 279 (DAIMLER X) AIRFOIL (goe279-il) Reynolds number: 100,000 Max Cl/Cd: 58.35 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe279-il-100000.txt Download as CSV file: xf-goe279-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3501 0.09431 0.08959 -0.0235 1.0000 0.0507
-7.250 -0.3530 0.09216 0.08752 -0.0233 1.0000 0.0519
-7.000 -0.3555 0.09005 0.08548 -0.0237 1.0000 0.0530
-6.750 -0.3568 0.08809 0.08356 -0.0253 1.0000 0.0542
-6.500 -0.3535 0.08655 0.08203 -0.0298 1.0000 0.0552
-6.250 -0.3432 0.08515 0.08051 -0.0355 1.0000 0.0557
-6.000 -0.3387 0.08081 0.07621 -0.0353 1.0000 0.0563
-5.750 -0.3396 0.07647 0.07197 -0.0309 1.0000 0.0573
-5.500 -0.3354 0.07338 0.06893 -0.0290 1.0000 0.0587
-5.250 -0.3271 0.07049 0.06604 -0.0290 1.0000 0.0606
-5.000 -0.3145 0.06755 0.06306 -0.0304 1.0000 0.0632
-4.750 -0.2732 0.06667 0.06166 -0.0400 1.0000 0.0685
-4.500 -0.2673 0.06115 0.05630 -0.0389 1.0000 0.0697
-4.250 -0.2604 0.05782 0.05308 -0.0372 1.0000 0.0722
-4.000 -0.2207 0.05778 0.05243 -0.0427 1.0000 0.0826
-3.750 -0.2143 0.05204 0.04697 -0.0417 1.0000 0.0849
-3.500 -0.1987 0.04936 0.04431 -0.0416 1.0000 0.0901
-3.250 -0.1692 0.04668 0.04135 -0.0446 1.0000 0.0996
-2.750 -0.1251 0.04186 0.03638 -0.0464 1.0000 0.1192
-2.500 -0.0963 0.04024 0.03443 -0.0486 1.0000 0.1430
-2.250 -0.0766 0.03780 0.03211 -0.0490 1.0000 0.1637
-1.000 0.1891 0.02690 0.01938 -0.0746 0.9644 0.1903
-0.750 0.2496 0.02520 0.01697 -0.0783 0.9578 0.1320
-0.500 0.2954 0.02416 0.01546 -0.0804 0.9469 0.1136
-0.250 0.3408 0.02338 0.01447 -0.0830 0.9364 0.1119
0.000 0.3920 0.02204 0.01309 -0.0868 0.9290 0.1105
0.250 0.4335 0.02110 0.01216 -0.0888 0.9171 0.1102
0.500 0.4769 0.02005 0.01125 -0.0912 0.9063 0.1149
0.750 0.5263 0.01906 0.01029 -0.0944 0.8986 0.1219
1.000 0.5646 0.01837 0.00957 -0.0955 0.8848 0.1298
1.250 0.6019 0.01764 0.00894 -0.0963 0.8705 0.1574
1.500 0.6319 0.01537 0.00848 -0.0952 0.8560 1.0000
1.750 0.6657 0.01501 0.00788 -0.0949 0.8392 1.0000
2.000 0.6936 0.01479 0.00753 -0.0938 0.8170 1.0000
2.250 0.7235 0.01450 0.00711 -0.0930 0.7950 1.0000
2.500 0.7502 0.01433 0.00684 -0.0918 0.7672 1.0000
2.750 0.7771 0.01420 0.00657 -0.0906 0.7363 1.0000
3.000 0.8035 0.01415 0.00637 -0.0893 0.7009 1.0000
3.250 0.8293 0.01427 0.00622 -0.0880 0.6626 1.0000
3.500 0.8542 0.01464 0.00629 -0.0868 0.6241 1.0000
3.750 0.8786 0.01514 0.00656 -0.0857 0.5885 1.0000
4.000 0.9027 0.01567 0.00687 -0.0847 0.5567 1.0000
4.250 0.9268 0.01617 0.00722 -0.0838 0.5286 1.0000
4.500 0.9512 0.01667 0.00758 -0.0831 0.5050 1.0000
4.750 0.9758 0.01716 0.00803 -0.0824 0.4838 1.0000
5.000 1.0005 0.01766 0.00844 -0.0817 0.4652 1.0000
5.250 1.0252 0.01818 0.00888 -0.0811 0.4480 1.0000
5.500 1.0495 0.01870 0.00939 -0.0805 0.4305 1.0000
5.750 1.0733 0.01921 0.00993 -0.0798 0.4125 1.0000
6.000 1.0968 0.01974 0.01043 -0.0790 0.3944 1.0000
6.250 1.1199 0.02030 0.01095 -0.0782 0.3765 1.0000
6.500 1.1430 0.02091 0.01150 -0.0774 0.3589 1.0000
6.750 1.1651 0.02152 0.01217 -0.0765 0.3404 1.0000
7.000 1.1866 0.02213 0.01282 -0.0755 0.3214 1.0000
7.250 1.2082 0.02276 0.01349 -0.0745 0.3037 1.0000
7.500 1.2294 0.02339 0.01416 -0.0735 0.2868 1.0000
7.750 1.2498 0.02395 0.01480 -0.0723 0.2703 1.0000
8.000 1.2703 0.02454 0.01549 -0.0712 0.2552 1.0000
8.250 1.2891 0.02503 0.01606 -0.0698 0.2391 1.0000
8.500 1.3064 0.02547 0.01670 -0.0682 0.2204 1.0000
8.750 1.3219 0.02595 0.01731 -0.0664 0.1988 1.0000
9.000 1.3343 0.02676 0.01812 -0.0642 0.1706 1.0000
9.250 1.3408 0.02844 0.01960 -0.0613 0.1378 1.0000
9.500 1.3471 0.03048 0.02146 -0.0584 0.1165 1.0000
9.750 1.3570 0.03228 0.02325 -0.0560 0.1036 1.0000
10.000 1.3694 0.03407 0.02513 -0.0539 0.0951 1.0000
10.250 1.3814 0.03584 0.02679 -0.0521 0.0883 1.0000
10.500 1.3932 0.03735 0.02860 -0.0499 0.0823 1.0000
10.750 1.4047 0.03902 0.03022 -0.0480 0.0776 1.0000
11.000 1.4154 0.04099 0.03243 -0.0459 0.0732 1.0000
11.250 1.4252 0.04283 0.03441 -0.0438 0.0693 1.0000
11.500 1.4430 0.04552 0.03704 -0.0431 0.0654 1.0000
11.750 1.4457 0.04784 0.03976 -0.0403 0.0629 1.0000
12.000 1.4483 0.05034 0.04253 -0.0378 0.0603 1.0000
12.250 1.4532 0.05311 0.04550 -0.0358 0.0583 1.0000
12.500 1.4660 0.05697 0.04938 -0.0351 0.0558 1.0000
12.750 1.4550 0.06053 0.05328 -0.0322 0.0550 1.0000
13.000 1.4391 0.06394 0.05705 -0.0296 0.0544 1.0000
13.250 1.4217 0.06788 0.06134 -0.0277 0.0540 1.0000
13.500 1.4022 0.07235 0.06613 -0.0267 0.0537 1.0000
13.750 1.3807 0.07742 0.07149 -0.0267 0.0536 1.0000
14.000 1.3576 0.08314 0.07749 -0.0277 0.0536 1.0000
14.250 1.3330 0.08961 0.08420 -0.0298 0.0539 1.0000
14.500 1.3073 0.09687 0.09168 -0.0331 0.0542 1.0000
14.750 1.2814 0.10482 0.09982 -0.0372 0.0547 1.0000
15.000 1.2556 0.11345 0.10859 -0.0421 0.0552 1.0000
15.250 1.0726 0.17430 0.16949 -0.0834 0.0779 1.0000
15.500 1.0768 0.17881 0.17402 -0.0847 0.0772 1.0000
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Polar data table (+)
Polar graphs
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