GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 277 (DAIMLER VIII) AIRFOIL (goe277-il) Reynolds number: 100,000 Max Cl/Cd: 55.73 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe277-il-100000-n5.txt Download as CSV file: xf-goe277-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 277 (DAIMLER VIII) 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 -0.3348 0.09763 0.09289 -0.0270 1.0000 0.0447
-7.750 -0.3413 0.09603 0.09140 -0.0294 1.0000 0.0453
-7.500 -0.3415 0.09369 0.08912 -0.0330 1.0000 0.0457
-7.250 -0.3387 0.09092 0.08639 -0.0361 1.0000 0.0459
-7.000 -0.3346 0.08786 0.08334 -0.0386 1.0000 0.0460
-6.750 -0.3339 0.08325 0.07881 -0.0375 1.0000 0.0465
-6.500 -0.3334 0.07966 0.07529 -0.0337 1.0000 0.0474
-6.250 -0.3306 0.07688 0.07256 -0.0319 1.0000 0.0483
-6.000 -0.3270 0.07420 0.06991 -0.0313 1.0000 0.0494
-5.750 -0.3220 0.07147 0.06720 -0.0315 1.0000 0.0507
-5.500 -0.2625 0.06633 0.06159 -0.0496 0.9916 0.0595
-5.250 -0.2413 0.06038 0.05571 -0.0523 0.9865 0.0611
-5.000 -0.2153 0.05665 0.05195 -0.0548 0.9800 0.0634
-4.750 -0.1797 0.05258 0.04772 -0.0602 0.9737 0.0667
-4.250 -0.0967 0.04221 0.03660 -0.0722 0.9595 0.0563
-4.000 -0.0573 0.03778 0.03182 -0.0766 0.9531 0.0525
-3.750 -0.0185 0.03454 0.02817 -0.0800 0.9451 0.0549
-3.500 0.0225 0.03108 0.02425 -0.0834 0.9373 0.0532
-3.250 0.0596 0.02826 0.02096 -0.0854 0.9255 0.0522
-3.000 0.0957 0.02620 0.01849 -0.0869 0.9123 0.0537
-2.750 0.1302 0.02449 0.01637 -0.0880 0.8982 0.0555
-2.500 0.1631 0.02287 0.01440 -0.0887 0.8845 0.0551
-2.250 0.1950 0.02154 0.01275 -0.0891 0.8706 0.0550
-2.000 0.2260 0.02040 0.01134 -0.0893 0.8555 0.0553
-1.750 0.2565 0.01942 0.01013 -0.0893 0.8395 0.0558
-1.500 0.2866 0.01858 0.00910 -0.0892 0.8224 0.0567
-1.250 0.3162 0.01806 0.00837 -0.0890 0.8041 0.0593
-1.000 0.3446 0.01725 0.00748 -0.0888 0.7849 0.0613
-0.750 0.3729 0.01664 0.00679 -0.0884 0.7655 0.0622
-0.500 0.4007 0.01616 0.00622 -0.0880 0.7463 0.0635
-0.250 0.4279 0.01582 0.00577 -0.0875 0.7266 0.0651
0.000 0.4551 0.01560 0.00541 -0.0870 0.7069 0.0674
0.250 0.4820 0.01545 0.00510 -0.0865 0.6871 0.0706
0.500 0.5088 0.01535 0.00486 -0.0860 0.6663 0.0752
0.750 0.5358 0.01525 0.00467 -0.0855 0.6451 0.0864
1.000 0.5609 0.01300 0.00463 -0.0848 0.6250 1.0000
1.250 0.5873 0.01319 0.00453 -0.0843 0.6035 1.0000
1.500 0.6135 0.01340 0.00449 -0.0837 0.5827 1.0000
1.750 0.6396 0.01364 0.00451 -0.0832 0.5620 1.0000
2.000 0.6656 0.01389 0.00457 -0.0828 0.5424 1.0000
2.250 0.6915 0.01417 0.00466 -0.0823 0.5245 1.0000
2.500 0.7175 0.01447 0.00479 -0.0819 0.5083 1.0000
2.750 0.7435 0.01477 0.00497 -0.0815 0.4932 1.0000
3.000 0.7695 0.01508 0.00517 -0.0811 0.4788 1.0000
3.250 0.7955 0.01539 0.00540 -0.0808 0.4655 1.0000
3.500 0.8215 0.01572 0.00566 -0.0805 0.4535 1.0000
3.750 0.8475 0.01605 0.00593 -0.0802 0.4432 1.0000
4.000 0.8735 0.01640 0.00623 -0.0799 0.4341 1.0000
4.250 0.8996 0.01674 0.00658 -0.0796 0.4252 1.0000
4.500 0.9255 0.01712 0.00690 -0.0793 0.4177 1.0000
4.750 0.9515 0.01748 0.00731 -0.0791 0.4094 1.0000
5.000 0.9774 0.01788 0.00770 -0.0788 0.4033 1.0000
5.250 1.0035 0.01827 0.00817 -0.0785 0.3966 1.0000
5.500 1.0291 0.01867 0.00858 -0.0782 0.3898 1.0000
5.750 1.0545 0.01907 0.00908 -0.0779 0.3823 1.0000
6.000 1.0798 0.01949 0.00953 -0.0775 0.3752 1.0000
6.250 1.1047 0.01990 0.01005 -0.0771 0.3673 1.0000
6.500 1.1294 0.02033 0.01051 -0.0767 0.3597 1.0000
6.750 1.1537 0.02074 0.01110 -0.0762 0.3509 1.0000
7.000 1.1774 0.02116 0.01156 -0.0756 0.3417 1.0000
7.250 1.2008 0.02156 0.01211 -0.0750 0.3317 1.0000
7.500 1.2242 0.02201 0.01271 -0.0744 0.3231 1.0000
7.750 1.2457 0.02238 0.01323 -0.0734 0.3094 1.0000
8.000 1.2656 0.02271 0.01368 -0.0723 0.2903 1.0000
8.250 1.2861 0.02311 0.01423 -0.0713 0.2735 1.0000
8.500 1.3059 0.02354 0.01480 -0.0701 0.2530 1.0000
8.750 1.3245 0.02407 0.01542 -0.0689 0.2200 1.0000
9.000 1.3358 0.02520 0.01627 -0.0669 0.1615 1.0000
9.250 1.3392 0.02735 0.01795 -0.0643 0.1073 1.0000
9.500 1.3440 0.02937 0.01979 -0.0618 0.0723 1.0000
9.750 1.3448 0.03154 0.02175 -0.0589 0.0397 1.0000
10.000 1.3442 0.03348 0.02369 -0.0557 0.0322 1.0000
10.500 1.3411 0.03753 0.02798 -0.0500 0.0268 1.0000
10.750 1.3390 0.03979 0.03044 -0.0478 0.0255 1.0000
11.000 1.3351 0.04240 0.03325 -0.0460 0.0245 1.0000
11.250 1.3294 0.04541 0.03645 -0.0448 0.0238 1.0000
11.500 1.3219 0.04891 0.04014 -0.0442 0.0231 1.0000
11.750 1.3129 0.05291 0.04431 -0.0443 0.0225 1.0000
12.000 1.3021 0.05740 0.04900 -0.0448 0.0220 1.0000
12.250 1.2907 0.06218 0.05394 -0.0457 0.0215 1.0000
12.500 1.2834 0.06654 0.05845 -0.0465 0.0211 1.0000
12.750 1.2771 0.07085 0.06293 -0.0474 0.0206 1.0000
13.000 1.2710 0.07515 0.06740 -0.0483 0.0201 1.0000
13.250 1.2655 0.07934 0.07174 -0.0490 0.0196 1.0000
13.500 1.2609 0.08338 0.07591 -0.0496 0.0192 1.0000
13.750 1.2580 0.08713 0.07979 -0.0501 0.0188 1.0000
14.000 1.2562 0.09068 0.08347 -0.0503 0.0184 1.0000
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Polar data table (+)
Polar graphs
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