GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 278 (DAIMLER IX) AIRFOIL (goe278-il) Reynolds number: 100,000 Max Cl/Cd: 56.38 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe278-il-100000-n5.txt Download as CSV file: xf-goe278-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3456 0.09816 0.09329 -0.0275 1.0000 0.0379
-7.750 -0.3528 0.09684 0.09209 -0.0286 1.0000 0.0383
-7.500 -0.3552 0.09505 0.09036 -0.0311 1.0000 0.0385
-7.250 -0.3550 0.09287 0.08822 -0.0333 1.0000 0.0387
-7.000 -0.3527 0.09036 0.08572 -0.0350 1.0000 0.0388
-6.750 -0.3486 0.08766 0.08300 -0.0363 1.0000 0.0388
-6.500 -0.3513 0.08271 0.07819 -0.0317 1.0000 0.0395
-6.250 -0.3503 0.07961 0.07514 -0.0289 1.0000 0.0403
-6.000 -0.3473 0.07686 0.07241 -0.0279 1.0000 0.0412
-5.750 -0.3422 0.07412 0.06967 -0.0279 1.0000 0.0422
-5.500 -0.3164 0.07014 0.06562 -0.0331 0.9961 0.0452
-5.000 -0.2403 0.06049 0.05559 -0.0500 0.9860 0.0516
-4.750 -0.2173 0.05696 0.05203 -0.0520 0.9811 0.0539
-4.500 -0.1635 0.05442 0.04891 -0.0611 0.9761 0.0622
-4.250 -0.1431 0.04941 0.04397 -0.0629 0.9708 0.0643
-4.000 -0.1150 0.04631 0.04083 -0.0653 0.9664 0.0690
-3.750 -0.0707 0.04367 0.03761 -0.0704 0.9609 0.0768
-3.500 -0.0439 0.04012 0.03410 -0.0723 0.9555 0.0797
-3.250 -0.0016 0.03757 0.03117 -0.0766 0.9512 0.0921
-2.750 0.0810 0.03117 0.02394 -0.0813 0.9377 0.0596
-2.500 0.1190 0.02886 0.02130 -0.0833 0.9283 0.0584
-2.250 0.1634 0.02659 0.01865 -0.0863 0.9212 0.0570
-2.000 0.1970 0.02480 0.01648 -0.0868 0.9101 0.0543
-1.750 0.2323 0.02326 0.01457 -0.0876 0.9014 0.0526
-1.500 0.2658 0.02203 0.01308 -0.0883 0.8931 0.0526
-1.250 0.2956 0.02114 0.01208 -0.0885 0.8829 0.0549
-1.000 0.3287 0.02015 0.01092 -0.0891 0.8742 0.0555
-0.750 0.3583 0.01928 0.00990 -0.0889 0.8626 0.0552
-0.500 0.3870 0.01851 0.00904 -0.0886 0.8499 0.0552
-0.250 0.4156 0.01782 0.00829 -0.0882 0.8363 0.0555
0.000 0.4437 0.01720 0.00763 -0.0878 0.8214 0.0561
0.250 0.4713 0.01664 0.00707 -0.0873 0.8053 0.0572
0.500 0.4989 0.01622 0.00662 -0.0868 0.7879 0.0604
0.750 0.5259 0.01586 0.00621 -0.0862 0.7678 0.0629
1.000 0.5529 0.01548 0.00576 -0.0856 0.7448 0.0648
1.250 0.5808 0.01525 0.00540 -0.0851 0.7193 0.0674
1.500 0.6089 0.01510 0.00508 -0.0847 0.6926 0.0713
2.000 0.6638 0.01499 0.00469 -0.0836 0.6397 0.0986
2.250 0.6912 0.01326 0.00468 -0.0834 0.6144 1.0000
2.750 0.7419 0.01384 0.00483 -0.0820 0.5644 1.0000
3.000 0.7671 0.01416 0.00498 -0.0813 0.5415 1.0000
3.250 0.7921 0.01447 0.00518 -0.0807 0.5190 1.0000
3.500 0.8169 0.01481 0.00538 -0.0801 0.4984 1.0000
3.750 0.8417 0.01516 0.00561 -0.0794 0.4788 1.0000
4.000 0.8663 0.01553 0.00589 -0.0788 0.4605 1.0000
4.250 0.8908 0.01591 0.00618 -0.0782 0.4432 1.0000
4.500 0.9153 0.01630 0.00650 -0.0776 0.4279 1.0000
4.750 0.9398 0.01669 0.00685 -0.0770 0.4142 1.0000
5.000 0.9640 0.01710 0.00723 -0.0764 0.3996 1.0000
5.250 0.9877 0.01752 0.00761 -0.0757 0.3838 1.0000
5.500 1.0112 0.01794 0.00801 -0.0750 0.3685 1.0000
5.750 1.0344 0.01836 0.00845 -0.0743 0.3529 1.0000
6.000 1.0571 0.01878 0.00887 -0.0735 0.3358 1.0000
6.250 1.0805 0.01920 0.00935 -0.0729 0.3227 1.0000
6.500 1.1037 0.01962 0.00984 -0.0721 0.3103 1.0000
6.750 1.1263 0.02004 0.01037 -0.0714 0.2945 1.0000
7.000 1.1489 0.02045 0.01090 -0.0706 0.2786 1.0000
7.250 1.1703 0.02090 0.01141 -0.0696 0.2548 1.0000
7.500 1.1908 0.02144 0.01196 -0.0686 0.2167 1.0000
7.750 1.2048 0.02265 0.01277 -0.0668 0.1561 1.0000
8.000 1.2153 0.02450 0.01412 -0.0648 0.0868 1.0000
8.250 1.2289 0.02594 0.01546 -0.0631 0.0719 1.0000
8.500 1.2426 0.02726 0.01682 -0.0613 0.0662 1.0000
8.750 1.2571 0.02840 0.01814 -0.0595 0.0626 1.0000
9.000 1.2691 0.02967 0.01960 -0.0575 0.0590 1.0000
9.250 1.2764 0.03121 0.02124 -0.0550 0.0558 1.0000
9.500 1.2824 0.03268 0.02285 -0.0523 0.0537 1.0000
9.750 1.2890 0.03403 0.02439 -0.0497 0.0517 1.0000
10.000 1.2941 0.03555 0.02605 -0.0471 0.0492 1.0000
10.250 1.2977 0.03725 0.02786 -0.0447 0.0469 1.0000
10.500 1.2995 0.03921 0.02990 -0.0423 0.0451 1.0000
10.750 1.3009 0.04154 0.03224 -0.0399 0.0430 1.0000
11.000 1.3083 0.04326 0.03420 -0.0383 0.0412 1.0000
11.250 1.3149 0.04523 0.03635 -0.0366 0.0392 1.0000
11.500 1.3207 0.04734 0.03861 -0.0351 0.0371 1.0000
11.750 1.3250 0.04958 0.04095 -0.0337 0.0352 1.0000
12.000 1.3320 0.05215 0.04350 -0.0323 0.0332 1.0000
12.250 1.3387 0.05487 0.04641 -0.0310 0.0319 1.0000
12.500 1.3392 0.05757 0.04945 -0.0298 0.0307 1.0000
12.750 1.3380 0.06054 0.05268 -0.0289 0.0294 1.0000
13.000 1.3352 0.06370 0.05609 -0.0283 0.0281 1.0000
13.250 1.3308 0.06712 0.05972 -0.0280 0.0271 1.0000
13.500 1.3259 0.07076 0.06355 -0.0280 0.0263 1.0000
13.750 1.3201 0.07466 0.06763 -0.0282 0.0257 1.0000
14.000 1.3137 0.07880 0.07194 -0.0287 0.0252 1.0000
14.250 1.3066 0.08315 0.07644 -0.0294 0.0247 1.0000
14.500 1.2979 0.08796 0.08140 -0.0304 0.0243 1.0000
14.750 1.2832 0.09367 0.08731 -0.0324 0.0240 1.0000
15.000 1.2661 0.09991 0.09380 -0.0354 0.0239 1.0000
15.250 1.2484 0.10671 0.10085 -0.0390 0.0238 1.0000
15.500 1.2306 0.11401 0.10836 -0.0433 0.0238 1.0000
15.750 1.2125 0.12180 0.11636 -0.0480 0.0238 1.0000
16.000 1.1942 0.13014 0.12487 -0.0533 0.0239 1.0000
16.250 1.1758 0.13902 0.13391 -0.0591 0.0239 1.0000
16.500 1.1578 0.14843 0.14345 -0.0653 0.0241 1.0000
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Polar data table (+)
Polar graphs
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