GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 281 (DAIMLER XII) AIRFOIL (goe281-il) Reynolds number: 100,000 Max Cl/Cd: 59.56 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe281-il-100000-n5.txt Download as CSV file: xf-goe281-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 281 (DAIMLER XII) 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3225 0.09663 0.09201 -0.0278 1.0000 0.0339
-7.500 -0.3303 0.09521 0.09071 -0.0282 1.0000 0.0346
-7.250 -0.3332 0.09349 0.08906 -0.0310 1.0000 0.0350
-7.000 -0.3322 0.09132 0.08695 -0.0340 1.0000 0.0353
-6.750 -0.3284 0.08874 0.08438 -0.0366 1.0000 0.0354
-6.500 -0.3294 0.08452 0.08025 -0.0347 1.0000 0.0359
-6.250 -0.3310 0.08125 0.07704 -0.0308 1.0000 0.0367
-6.000 -0.3184 0.07768 0.07348 -0.0317 0.9972 0.0380
-5.750 -0.2907 0.07323 0.06896 -0.0376 0.9914 0.0402
-5.500 -0.2513 0.06825 0.06383 -0.0478 0.9851 0.0446
-5.250 -0.2146 0.06267 0.05810 -0.0568 0.9783 0.0483
-5.000 -0.1899 0.05926 0.05466 -0.0593 0.9727 0.0528
-4.750 -0.1391 0.05398 0.04896 -0.0705 0.9663 0.0602
-4.500 -0.1167 0.05057 0.04561 -0.0718 0.9604 0.0638
-4.250 -0.0762 0.04662 0.04134 -0.0780 0.9541 0.0753
-4.000 -0.0371 0.04331 0.03771 -0.0830 0.9477 0.0883
-3.750 -0.0065 0.04035 0.03471 -0.0852 0.9402 0.0954
-3.500 0.0282 0.03743 0.03156 -0.0884 0.9325 0.1083
-3.000 0.1139 0.02982 0.02257 -0.0929 0.9162 0.0572
-2.750 0.1491 0.02733 0.01976 -0.0946 0.9085 0.0542
-2.500 0.1808 0.02571 0.01776 -0.0952 0.8975 0.0555
-2.250 0.2135 0.02410 0.01581 -0.0959 0.8872 0.0549
-2.000 0.2468 0.02260 0.01396 -0.0965 0.8772 0.0532
-1.750 0.2784 0.02137 0.01244 -0.0968 0.8661 0.0520
-1.500 0.3087 0.02037 0.01118 -0.0968 0.8546 0.0513
-1.250 0.3389 0.01949 0.01010 -0.0969 0.8438 0.0510
-1.000 0.3690 0.01872 0.00919 -0.0969 0.8331 0.0513
-0.750 0.3987 0.01812 0.00849 -0.0969 0.8224 0.0542
-0.500 0.4268 0.01759 0.00787 -0.0967 0.8101 0.0556
-0.250 0.4547 0.01707 0.00731 -0.0964 0.7979 0.0556
0.000 0.4824 0.01664 0.00684 -0.0961 0.7857 0.0557
0.250 0.5102 0.01630 0.00644 -0.0958 0.7735 0.0560
0.500 0.5378 0.01605 0.00609 -0.0955 0.7614 0.0564
0.750 0.5653 0.01588 0.00582 -0.0951 0.7489 0.0572
1.000 0.5927 0.01578 0.00560 -0.0947 0.7350 0.0582
1.250 0.6201 0.01570 0.00541 -0.0943 0.7199 0.0599
1.500 0.6472 0.01563 0.00524 -0.0939 0.7032 0.0635
1.750 0.6737 0.01562 0.00513 -0.0933 0.6837 0.0717
2.000 0.6982 0.01367 0.00516 -0.0925 0.6653 1.0000
2.250 0.7246 0.01385 0.00514 -0.0919 0.6481 1.0000
2.500 0.7510 0.01405 0.00518 -0.0915 0.6326 1.0000
2.750 0.7773 0.01427 0.00529 -0.0910 0.6169 1.0000
3.000 0.8034 0.01449 0.00541 -0.0906 0.6009 1.0000
3.250 0.8292 0.01472 0.00557 -0.0901 0.5838 1.0000
3.500 0.8549 0.01496 0.00578 -0.0897 0.5658 1.0000
3.750 0.8805 0.01520 0.00598 -0.0892 0.5470 1.0000
4.000 0.9056 0.01545 0.00617 -0.0886 0.5265 1.0000
4.250 0.9303 0.01572 0.00638 -0.0880 0.5032 1.0000
4.500 0.9544 0.01604 0.00660 -0.0873 0.4794 1.0000
4.750 0.9780 0.01642 0.00686 -0.0865 0.4557 1.0000
5.000 1.0015 0.01686 0.00719 -0.0857 0.4338 1.0000
5.250 1.0252 0.01730 0.00762 -0.0851 0.4150 1.0000
5.500 1.0489 0.01776 0.00807 -0.0844 0.3976 1.0000
5.750 1.0725 0.01822 0.00854 -0.0838 0.3804 1.0000
6.000 1.0955 0.01867 0.00904 -0.0831 0.3592 1.0000
6.250 1.1166 0.01919 0.00952 -0.0821 0.3246 1.0000
6.500 1.1366 0.01980 0.01000 -0.0810 0.2888 1.0000
6.750 1.1559 0.02054 0.01059 -0.0799 0.2562 1.0000
7.000 1.1754 0.02130 0.01127 -0.0788 0.2333 1.0000
7.250 1.1932 0.02222 0.01204 -0.0775 0.1986 1.0000
7.500 1.2116 0.02311 0.01286 -0.0764 0.1642 1.0000
7.750 1.2288 0.02411 0.01371 -0.0750 0.1326 1.0000
8.000 1.2416 0.02557 0.01486 -0.0732 0.0839 1.0000
8.250 1.2452 0.02794 0.01675 -0.0703 0.0289 1.0000
8.500 1.2588 0.02921 0.01817 -0.0683 0.0260 1.0000
8.750 1.2709 0.03057 0.01972 -0.0662 0.0241 1.0000
9.000 1.2794 0.03218 0.02158 -0.0637 0.0222 1.0000
9.250 1.2866 0.03367 0.02328 -0.0611 0.0209 1.0000
9.500 1.2924 0.03515 0.02499 -0.0584 0.0200 1.0000
9.750 1.2961 0.03685 0.02691 -0.0557 0.0195 1.0000
10.000 1.2977 0.03876 0.02904 -0.0531 0.0191 1.0000
10.250 1.2976 0.04090 0.03139 -0.0508 0.0187 1.0000
10.500 1.2959 0.04328 0.03398 -0.0487 0.0184 1.0000
10.750 1.2931 0.04592 0.03681 -0.0470 0.0181 1.0000
11.000 1.2894 0.04881 0.03988 -0.0457 0.0178 1.0000
11.250 1.2856 0.05189 0.04314 -0.0447 0.0175 1.0000
11.500 1.2815 0.05516 0.04660 -0.0440 0.0170 1.0000
11.750 1.2777 0.05854 0.05012 -0.0436 0.0165 1.0000
12.000 1.2740 0.06200 0.05371 -0.0433 0.0160 1.0000
12.250 1.2709 0.06547 0.05730 -0.0430 0.0156 1.0000
12.500 1.2691 0.06882 0.06076 -0.0426 0.0151 1.0000
12.750 1.2698 0.07188 0.06391 -0.0419 0.0149 1.0000
13.000 1.2726 0.07477 0.06690 -0.0411 0.0146 1.0000
13.250 1.2763 0.07766 0.06991 -0.0402 0.0144 1.0000
13.500 1.2796 0.08075 0.07314 -0.0395 0.0143 1.0000
13.750 1.2805 0.08425 0.07680 -0.0392 0.0142 1.0000
14.000 1.2792 0.08813 0.08087 -0.0393 0.0141 1.0000
14.250 1.2747 0.09246 0.08540 -0.0400 0.0141 1.0000
14.500 1.2683 0.09715 0.09031 -0.0412 0.0140 1.0000
14.750 1.2604 0.10221 0.09558 -0.0429 0.0140 1.0000
15.000 1.2512 0.10765 0.10126 -0.0452 0.0140 1.0000
15.250 1.2411 0.11345 0.10728 -0.0481 0.0141 1.0000
15.500 1.2303 0.11964 0.11368 -0.0515 0.0141 1.0000
15.750 1.2189 0.12626 0.12051 -0.0554 0.0142 1.0000
16.000 1.2072 0.13332 0.12777 -0.0599 0.0143 1.0000
16.250 1.1951 0.14088 0.13552 -0.0649 0.0144 1.0000
16.500 1.1825 0.14904 0.14387 -0.0705 0.0145 1.0000
16.750 1.1694 0.15790 0.15288 -0.0767 0.0147 1.0000
17.000 1.1555 0.16772 0.16287 -0.0835 0.0149 1.0000
17.250 1.1409 0.17870 0.17399 -0.0909 0.0152 1.0000
17.500 1.1233 0.19220 0.18760 -0.0995 0.0157 1.0000
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Polar data table (+)
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