GOE 610 B AIRFOIL (goe610b-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 610 B AIRFOIL (goe610b-il) Reynolds number: 100,000 Max Cl/Cd: 62.67 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe610b-il-100000-n5.txt Download as CSV file: xf-goe610b-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 610 B 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.2864 0.10376 0.09907 -0.0362 1.0000 0.0421
-8.250 -0.2913 0.10194 0.09736 -0.0352 1.0000 0.0422
-8.000 -0.3021 0.10073 0.09626 -0.0332 1.0000 0.0422
-7.750 -0.2989 0.09812 0.09371 -0.0357 0.9940 0.0423
-7.500 -0.2804 0.09401 0.08959 -0.0431 0.9824 0.0425
-7.250 -0.2597 0.08954 0.08510 -0.0504 0.9720 0.0426
-7.000 -0.2375 0.08479 0.08031 -0.0564 0.9642 0.0426
-6.750 -0.2190 0.08033 0.07582 -0.0602 0.9549 0.0425
-6.500 -0.2020 0.07578 0.07127 -0.0597 0.9508 0.0406
-6.250 -0.1810 0.07159 0.06703 -0.0652 0.9403 0.0407
-6.000 -0.1495 0.06661 0.06190 -0.0756 0.9300 0.0423
-5.750 -0.1261 0.06226 0.05746 -0.0793 0.9227 0.0418
-5.500 -0.1031 0.05811 0.05320 -0.0832 0.9132 0.0415
-5.250 -0.0775 0.05530 0.05033 -0.0860 0.9065 0.0476
-5.000 -0.0489 0.05140 0.04621 -0.0909 0.8962 0.0517
-4.750 -0.0231 0.04910 0.04382 -0.0934 0.8888 0.0653
-4.500 0.0068 0.04384 0.03820 -0.0973 0.8797 0.0553
-4.250 0.0343 0.04106 0.03515 -0.0992 0.8713 0.0599
-4.000 0.0627 0.03759 0.03137 -0.1010 0.8637 0.0589
-3.750 0.0908 0.03419 0.02742 -0.1022 0.8547 0.0628
-3.500 0.1174 0.03260 0.02574 -0.1029 0.8478 0.0656
-3.250 0.1426 0.03000 0.02271 -0.1029 0.8383 0.0647
-3.000 0.1705 0.02800 0.02032 -0.1031 0.8306 0.0651
-2.750 0.1966 0.02683 0.01888 -0.1030 0.8214 0.0695
-2.500 0.2232 0.02530 0.01697 -0.1027 0.8126 0.0697
-2.250 0.2509 0.02385 0.01519 -0.1025 0.8045 0.0688
-2.000 0.2764 0.02266 0.01368 -0.1020 0.7950 0.0682
-1.750 0.3051 0.02152 0.01221 -0.1019 0.7878 0.0681
-1.500 0.3303 0.02066 0.01111 -0.1012 0.7779 0.0684
-1.250 0.3577 0.01986 0.01007 -0.1008 0.7701 0.0693
-1.000 0.3842 0.01920 0.00922 -0.1004 0.7613 0.0707
-0.750 0.4108 0.01868 0.00852 -0.0999 0.7531 0.0721
-0.500 0.4374 0.01815 0.00796 -0.0996 0.7452 0.0739
-0.250 0.4629 0.01784 0.00765 -0.0991 0.7367 0.0761
0.000 0.4898 0.01765 0.00741 -0.0988 0.7296 0.0814
0.250 0.5153 0.01746 0.00718 -0.0982 0.7211 0.0850
0.500 0.5420 0.01711 0.00681 -0.0978 0.7139 0.0863
0.750 0.5670 0.01690 0.00660 -0.0972 0.7041 0.0874
1.000 0.5944 0.01671 0.00635 -0.0969 0.6956 0.0891
1.250 0.6211 0.01659 0.00617 -0.0964 0.6867 0.0916
1.500 0.6476 0.01653 0.00604 -0.0960 0.6785 0.0953
1.750 0.6746 0.01646 0.00593 -0.0957 0.6708 0.1009
2.000 0.7007 0.01643 0.00593 -0.0953 0.6629 0.1146
2.250 0.7277 0.01625 0.00591 -0.0950 0.6559 0.1754
2.750 0.8091 0.01495 0.00603 -0.1006 0.6379 1.0000
3.000 0.8328 0.01511 0.00613 -0.0996 0.6271 1.0000
3.250 0.8565 0.01528 0.00626 -0.0987 0.6165 1.0000
3.500 0.8807 0.01545 0.00635 -0.0978 0.6060 1.0000
3.750 0.9046 0.01563 0.00650 -0.0968 0.5953 1.0000
4.000 0.9278 0.01585 0.00675 -0.0959 0.5861 1.0000
4.250 0.9528 0.01606 0.00694 -0.0953 0.5789 1.0000
4.500 0.9756 0.01632 0.00727 -0.0943 0.5700 1.0000
4.750 0.9997 0.01654 0.00754 -0.0935 0.5619 1.0000
5.000 1.0224 0.01679 0.00786 -0.0925 0.5517 1.0000
5.250 1.0448 0.01704 0.00817 -0.0914 0.5404 1.0000
5.500 1.0669 0.01728 0.00850 -0.0903 0.5280 1.0000
5.750 1.0890 0.01753 0.00881 -0.0891 0.5158 1.0000
6.000 1.1106 0.01780 0.00918 -0.0879 0.5029 1.0000
6.250 1.1312 0.01808 0.00959 -0.0866 0.4884 1.0000
6.500 1.1512 0.01837 0.01002 -0.0851 0.4715 1.0000
6.750 1.1698 0.01869 0.01048 -0.0834 0.4495 1.0000
7.000 1.1873 0.01902 0.01086 -0.0815 0.4201 1.0000
7.250 1.2038 0.01944 0.01123 -0.0794 0.3902 1.0000
7.500 1.2187 0.01998 0.01168 -0.0772 0.3659 1.0000
7.750 1.2296 0.02077 0.01231 -0.0743 0.3382 1.0000
8.000 1.2380 0.02175 0.01311 -0.0713 0.3102 1.0000
8.250 1.2465 0.02271 0.01399 -0.0684 0.2823 1.0000
8.500 1.2546 0.02363 0.01488 -0.0655 0.2531 1.0000
8.750 1.2587 0.02462 0.01578 -0.0621 0.2165 1.0000
9.000 1.2582 0.02593 0.01682 -0.0582 0.1596 1.0000
9.250 1.2527 0.02777 0.01825 -0.0542 0.1273 1.0000
9.500 1.2530 0.02946 0.01984 -0.0512 0.1097 1.0000
9.750 1.2601 0.03081 0.02133 -0.0489 0.0763 1.0000
10.250 1.2553 0.03514 0.02530 -0.0435 0.0402 1.0000
10.500 1.2552 0.03724 0.02748 -0.0413 0.0352 1.0000
10.750 1.2554 0.03939 0.02972 -0.0393 0.0321 1.0000
11.000 1.2547 0.04170 0.03214 -0.0376 0.0296 1.0000
11.250 1.2531 0.04416 0.03470 -0.0361 0.0277 1.0000
11.500 1.2523 0.04666 0.03737 -0.0348 0.0261 1.0000
11.750 1.2501 0.04941 0.04026 -0.0336 0.0249 1.0000
12.000 1.2482 0.05219 0.04318 -0.0326 0.0240 1.0000
12.250 1.2458 0.05513 0.04623 -0.0318 0.0233 1.0000
12.500 1.2416 0.05834 0.04951 -0.0311 0.0225 1.0000
12.750 1.2419 0.06113 0.05242 -0.0303 0.0217 1.0000
13.000 1.2450 0.06372 0.05519 -0.0296 0.0210 1.0000
13.250 1.2480 0.06640 0.05806 -0.0289 0.0201 1.0000
13.500 1.2511 0.06915 0.06107 -0.0282 0.0193 1.0000
13.750 1.2547 0.07197 0.06408 -0.0276 0.0188 1.0000
14.000 1.2575 0.07502 0.06732 -0.0271 0.0183 1.0000
14.250 1.2585 0.07837 0.07088 -0.0268 0.0179 1.0000
14.500 1.2570 0.08212 0.07486 -0.0269 0.0176 1.0000
14.750 1.2528 0.08629 0.07926 -0.0274 0.0173 1.0000
15.000 1.2464 0.09087 0.08407 -0.0284 0.0170 1.0000
15.250 1.2377 0.09589 0.08931 -0.0298 0.0167 1.0000
15.500 1.2281 0.10122 0.09486 -0.0317 0.0166 1.0000
15.750 1.2163 0.10709 0.10094 -0.0341 0.0163 1.0000
16.000 1.2039 0.11331 0.10738 -0.0371 0.0161 1.0000
16.250 1.1903 0.12011 0.11439 -0.0405 0.0160 1.0000
16.500 1.1747 0.12781 0.12231 -0.0448 0.0161 1.0000
16.750 1.1573 0.13645 0.13117 -0.0500 0.0163 1.0000
17.000 1.1363 0.14683 0.14177 -0.0565 0.0166 1.0000
17.250 1.1072 0.16076 0.15590 -0.0653 0.0175 1.0000
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