GOE 256 (JUNKERS E) AIRFOIL (goe256-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 256 (JUNKERS E) AIRFOIL (goe256-il) Reynolds number: 100,000 Max Cl/Cd: 45.18 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe256-il-100000.txt Download as CSV file: xf-goe256-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 256 (JUNKERS E) 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2897 0.11186 0.10715 -0.0494 0.9743 0.1303
-8.500 -0.3015 0.10891 0.10422 -0.0555 0.9694 0.1365
-8.250 -0.3589 0.10754 0.10293 -0.0591 0.9590 0.1377
-8.000 -0.3098 0.10211 0.09748 -0.0577 0.9585 0.1405
-7.750 -0.2806 0.09914 0.09448 -0.0584 0.9560 0.1443
-7.500 -0.2855 0.09697 0.09234 -0.0583 0.9499 0.1479
-7.250 -0.3160 0.09448 0.08987 -0.0605 0.9417 0.1524
-7.000 -0.3655 0.09043 0.08573 -0.0639 0.9309 0.1558
-6.750 -0.3301 0.08763 0.08302 -0.0617 0.9282 0.1583
-6.500 -0.3047 0.08495 0.08033 -0.0628 0.9244 0.1634
-6.250 -0.3550 0.08188 0.07695 -0.0653 0.9125 0.1731
-6.000 -0.3201 0.07845 0.07370 -0.0644 0.9092 0.1760
-5.750 -0.3344 0.07730 0.07214 -0.0662 0.9002 0.1905
-5.500 -0.3108 0.07332 0.06842 -0.0643 0.8951 0.1932
-5.250 -0.2809 0.07104 0.06616 -0.0653 0.8904 0.2020
-5.000 -0.2783 0.06838 0.06340 -0.0649 0.8827 0.2130
-4.750 -0.2691 0.06613 0.06100 -0.0652 0.8749 0.2289
-4.500 -0.2365 0.06341 0.05820 -0.0678 0.8707 0.2473
-4.250 -0.2334 0.05159 0.04426 -0.0699 0.8616 0.1382
-4.000 -0.2025 0.05146 0.04488 -0.0716 0.8557 0.1689
-3.750 -0.1589 0.04417 0.03572 -0.0736 0.8528 0.1223
-3.500 -0.1493 0.04311 0.03445 -0.0709 0.8426 0.1224
-3.250 -0.1120 0.04055 0.03177 -0.0731 0.8378 0.1251
-3.000 -0.0637 0.03884 0.02985 -0.0763 0.8345 0.1278
-2.750 -0.0547 0.03838 0.02925 -0.0734 0.8229 0.1290
-2.500 -0.0102 0.03718 0.02778 -0.0757 0.8186 0.1342
-2.250 0.0082 0.03691 0.02727 -0.0740 0.8083 0.1371
-2.000 0.0488 0.03546 0.02578 -0.0759 0.8029 0.1420
-1.750 0.0981 0.03429 0.02456 -0.0790 0.7999 0.1503
-1.500 0.1104 0.03431 0.02447 -0.0764 0.7873 0.1541
-1.250 0.1574 0.03291 0.02320 -0.0790 0.7838 0.1641
-1.000 0.1748 0.03286 0.02312 -0.0772 0.7724 0.1708
-0.750 0.2171 0.03167 0.02209 -0.0790 0.7678 0.1843
-0.500 0.2669 0.03031 0.02086 -0.0817 0.7655 0.2055
0.250 0.5126 0.02612 0.01893 -0.1090 0.7535 1.0000
0.500 0.5575 0.02527 0.01788 -0.1111 0.7492 1.0000
0.750 0.5714 0.02542 0.01794 -0.1083 0.7374 1.0000
1.000 0.6132 0.02464 0.01701 -0.1099 0.7321 1.0000
1.250 0.6310 0.02469 0.01698 -0.1078 0.7210 1.0000
1.500 0.6694 0.02404 0.01619 -0.1089 0.7146 1.0000
1.750 0.6880 0.02407 0.01616 -0.1068 0.7034 1.0000
2.000 0.7263 0.02343 0.01538 -0.1079 0.6965 1.0000
2.250 0.7424 0.02357 0.01547 -0.1056 0.6845 1.0000
2.500 0.7827 0.02292 0.01469 -0.1071 0.6779 1.0000
2.750 0.7947 0.02324 0.01497 -0.1041 0.6653 1.0000
3.000 0.8376 0.02257 0.01416 -0.1061 0.6592 1.0000
3.250 0.8471 0.02296 0.01454 -0.1027 0.6463 1.0000
3.500 0.8721 0.02290 0.01441 -0.1019 0.6369 1.0000
3.750 0.8986 0.02279 0.01422 -0.1013 0.6276 1.0000
4.000 0.9152 0.02306 0.01447 -0.0992 0.6174 1.0000
4.250 0.9472 0.02287 0.01418 -0.0997 0.6098 1.0000
4.500 0.9605 0.02332 0.01463 -0.0971 0.5998 1.0000
4.750 0.9944 0.02313 0.01433 -0.0979 0.5926 1.0000
5.000 1.0057 0.02367 0.01488 -0.0950 0.5830 1.0000
5.250 1.0388 0.02359 0.01471 -0.0957 0.5761 1.0000
5.500 1.0508 0.02422 0.01537 -0.0931 0.5677 1.0000
5.750 1.0771 0.02444 0.01554 -0.0928 0.5609 1.0000
6.000 1.1006 0.02485 0.01592 -0.0921 0.5544 1.0000
6.250 1.1132 0.02549 0.01661 -0.0896 0.5468 1.0000
6.500 1.1519 0.02551 0.01652 -0.0914 0.5412 1.0000
6.750 1.1531 0.02655 0.01767 -0.0872 0.5339 1.0000
7.000 1.1757 0.02702 0.01816 -0.0864 0.5278 1.0000
7.250 1.2081 0.02727 0.01834 -0.0873 0.5218 1.0000
7.500 1.2094 0.02821 0.01939 -0.0830 0.5138 1.0000
7.750 1.2583 0.02785 0.01885 -0.0863 0.5061 1.0000
8.000 1.2491 0.02902 0.02021 -0.0804 0.4981 1.0000
8.250 1.2857 0.02898 0.02008 -0.0817 0.4907 1.0000
8.500 1.2902 0.02989 0.02111 -0.0781 0.4833 1.0000
8.750 1.3114 0.03024 0.02147 -0.0771 0.4756 1.0000
9.000 1.3381 0.03066 0.02187 -0.0770 0.4691 1.0000
9.250 1.3374 0.03172 0.02309 -0.0728 0.4623 1.0000
9.500 1.3754 0.03176 0.02307 -0.0744 0.4558 1.0000
9.750 1.3762 0.03287 0.02433 -0.0705 0.4493 1.0000
10.000 1.3866 0.03359 0.02515 -0.0680 0.4424 1.0000
10.250 1.4293 0.03357 0.02505 -0.0704 0.4357 1.0000
10.500 1.4093 0.03509 0.02681 -0.0635 0.4289 1.0000
10.750 1.4492 0.03490 0.02657 -0.0652 0.4212 1.0000
11.000 1.4405 0.03612 0.02794 -0.0600 0.4144 1.0000
11.250 1.4508 0.03665 0.02854 -0.0575 0.4065 1.0000
11.500 1.4694 0.03706 0.02899 -0.0563 0.3986 1.0000
11.750 1.4622 0.03820 0.03026 -0.0517 0.3906 1.0000
12.000 1.4891 0.03822 0.03028 -0.0515 0.3819 1.0000
12.250 1.4770 0.03959 0.03179 -0.0466 0.3733 1.0000
12.500 1.4923 0.03993 0.03216 -0.0450 0.3637 1.0000
12.750 1.5049 0.04021 0.03246 -0.0431 0.3533 1.0000
13.000 1.4872 0.04215 0.03455 -0.0384 0.3436 1.0000
13.250 1.5103 0.04195 0.03426 -0.0375 0.3320 1.0000
13.500 1.4997 0.04358 0.03599 -0.0338 0.3213 1.0000
13.750 1.4889 0.04553 0.03803 -0.0306 0.3107 1.0000
14.000 1.5032 0.04583 0.03826 -0.0292 0.2993 1.0000
14.250 1.4940 0.04780 0.04030 -0.0264 0.2888 1.0000
14.500 1.4826 0.05023 0.04282 -0.0239 0.2792 1.0000
14.750 1.4955 0.05065 0.04312 -0.0227 0.2689 1.0000
15.000 1.4743 0.05421 0.04686 -0.0202 0.2604 1.0000
15.250 1.4779 0.05568 0.04830 -0.0190 0.2516 1.0000
15.500 1.4693 0.05847 0.05120 -0.0175 0.2437 1.0000
15.750 1.4709 0.06044 0.05319 -0.0165 0.2363 1.0000
16.000 1.4629 0.06350 0.05635 -0.0155 0.2293 1.0000
16.250 1.4682 0.06518 0.05802 -0.0148 0.2223 1.0000
16.500 1.4545 0.06911 0.06211 -0.0141 0.2160 1.0000
16.750 1.4665 0.07006 0.06297 -0.0135 0.2087 1.0000
17.000 1.4465 0.07501 0.06813 -0.0133 0.2033 1.0000
17.250 1.4641 0.07520 0.06817 -0.0127 0.1953 1.0000
17.500 1.4391 0.08105 0.07430 -0.0131 0.1906 1.0000
17.750 1.4436 0.08301 0.07623 -0.0129 0.1836 1.0000
18.000 1.4359 0.08679 0.08012 -0.0131 0.1782 1.0000
18.250 1.4236 0.09129 0.08476 -0.0138 0.1725 1.0000
18.500 1.4301 0.09302 0.08644 -0.0137 0.1652 1.0000
18.750 1.4080 0.09913 0.09277 -0.0151 0.1600 1.0000
19.000 1.4136 0.10094 0.09451 -0.0153 0.1514 1.0000
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