RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il) Reynolds number: 100,000 Max Cl/Cd: 46.81 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-amsoil1-il-100000-n5.txt Download as CSV file: xf-amsoil1-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RUTAN CANARD 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5270 0.08543 0.07991 -0.0396 1.0000 0.0475
-9.500 -0.5360 0.07857 0.07309 -0.0453 1.0000 0.0473
-9.250 -0.5537 0.07162 0.06611 -0.0507 1.0000 0.0470
-9.000 -0.5743 0.06563 0.06002 -0.0530 1.0000 0.0469
-8.750 -0.5950 0.05979 0.05402 -0.0535 1.0000 0.0469
-8.500 -0.6215 0.05473 0.04870 -0.0508 1.0000 0.0471
-8.250 -0.6375 0.04957 0.04313 -0.0489 0.9968 0.0477
-8.000 -0.6095 0.04857 0.04213 -0.0507 0.9910 0.0487
-7.750 -0.5878 0.04523 0.03850 -0.0530 0.9844 0.0498
-7.500 -0.5685 0.04099 0.03378 -0.0548 0.9773 0.0508
-7.250 -0.5449 0.03692 0.02911 -0.0566 0.9719 0.0522
-7.000 -0.5229 0.03339 0.02487 -0.0574 0.9647 0.0543
-6.750 -0.4924 0.03215 0.02356 -0.0589 0.9599 0.0556
-6.500 -0.4641 0.03059 0.02178 -0.0598 0.9544 0.0570
-6.250 -0.4361 0.02890 0.01977 -0.0604 0.9483 0.0587
-6.000 -0.4053 0.02717 0.01757 -0.0614 0.9438 0.0614
-5.750 -0.3784 0.02633 0.01674 -0.0617 0.9374 0.0631
-5.500 -0.3493 0.02535 0.01564 -0.0622 0.9318 0.0652
-5.250 -0.3181 0.02428 0.01436 -0.0630 0.9276 0.0678
-5.000 -0.2924 0.02347 0.01345 -0.0627 0.9207 0.0706
-4.750 -0.2641 0.02283 0.01281 -0.0630 0.9152 0.0735
-4.500 -0.2339 0.02207 0.01194 -0.0634 0.9110 0.0769
-4.250 -0.2086 0.02146 0.01131 -0.0630 0.9041 0.0804
-4.000 -0.1812 0.02096 0.01083 -0.0631 0.8985 0.0849
-3.750 -0.1523 0.02040 0.01019 -0.0631 0.8942 0.0899
-3.500 -0.1275 0.01995 0.00984 -0.0627 0.8878 0.0951
-3.250 -0.1009 0.01956 0.00941 -0.0624 0.8820 0.1021
-3.000 -0.0738 0.01912 0.00905 -0.0623 0.8774 0.1098
-2.750 -0.0483 0.01878 0.00875 -0.0619 0.8716 0.1189
-2.500 -0.0226 0.01852 0.00849 -0.0615 0.8655 0.1305
-2.250 0.0041 0.01816 0.00822 -0.0612 0.8608 0.1447
-2.000 0.0306 0.01785 0.00798 -0.0610 0.8562 0.1634
-1.750 0.0551 0.01754 0.00784 -0.0606 0.8496 0.1902
-1.500 0.0807 0.01704 0.00762 -0.0603 0.8445 0.2473
-1.250 0.0951 0.01540 0.00777 -0.0575 0.8405 0.6571
-1.000 0.1139 0.01547 0.00812 -0.0546 0.8342 0.7693
-0.750 0.1353 0.01558 0.00829 -0.0523 0.8285 0.8232
-0.500 0.1588 0.01565 0.00836 -0.0503 0.8242 0.8620
-0.250 0.1837 0.01575 0.00846 -0.0489 0.8195 0.8944
0.000 0.2130 0.01590 0.00860 -0.0485 0.8135 0.9227
0.250 0.2532 0.01597 0.00864 -0.0503 0.8093 0.9495
0.500 0.3087 0.01599 0.00862 -0.0552 0.8064 0.9742
0.750 0.3595 0.01596 0.00855 -0.0597 0.8033 0.9867
1.000 0.3957 0.01608 0.00868 -0.0620 0.7965 0.9943
1.250 0.4300 0.01610 0.00869 -0.0636 0.7912 1.0000
1.500 0.4519 0.01610 0.00866 -0.0625 0.7866 1.0000
1.750 0.4704 0.01630 0.00889 -0.0612 0.7790 1.0000
2.000 0.4912 0.01633 0.00891 -0.0599 0.7720 1.0000
2.250 0.5109 0.01624 0.00882 -0.0581 0.7609 1.0000
2.500 0.5325 0.01591 0.00843 -0.0561 0.7471 1.0000
2.750 0.5541 0.01561 0.00807 -0.0541 0.7310 1.0000
3.000 0.5762 0.01540 0.00783 -0.0524 0.7142 1.0000
3.250 0.5980 0.01526 0.00768 -0.0508 0.6938 1.0000
3.500 0.6208 0.01515 0.00754 -0.0493 0.6707 1.0000
3.750 0.6448 0.01505 0.00741 -0.0481 0.6475 1.0000
4.000 0.6683 0.01507 0.00742 -0.0470 0.6205 1.0000
4.250 0.6918 0.01511 0.00738 -0.0457 0.5836 1.0000
4.500 0.7139 0.01525 0.00728 -0.0441 0.5203 1.0000
4.750 0.7285 0.01604 0.00729 -0.0415 0.3863 1.0000
5.250 0.7531 0.01873 0.00872 -0.0373 0.1998 1.0000
5.500 0.7715 0.01961 0.00939 -0.0361 0.1695 1.0000
5.750 0.7910 0.02038 0.01003 -0.0350 0.1495 1.0000
6.000 0.8106 0.02112 0.01068 -0.0339 0.1351 1.0000
6.250 0.8299 0.02188 0.01136 -0.0328 0.1243 1.0000
6.500 0.8494 0.02263 0.01206 -0.0317 0.1151 1.0000
6.750 0.8690 0.02338 0.01280 -0.0306 0.1076 1.0000
7.000 0.8877 0.02420 0.01355 -0.0294 0.1013 1.0000
7.250 0.9075 0.02498 0.01437 -0.0284 0.0956 1.0000
7.500 0.9267 0.02581 0.01517 -0.0273 0.0909 1.0000
7.750 0.9461 0.02672 0.01606 -0.0263 0.0868 1.0000
8.000 0.9663 0.02757 0.01697 -0.0253 0.0826 1.0000
8.250 0.9858 0.02850 0.01785 -0.0244 0.0794 1.0000
8.500 1.0067 0.02952 0.01890 -0.0236 0.0765 1.0000
8.750 1.0277 0.03048 0.01996 -0.0228 0.0733 1.0000
9.000 1.0476 0.03146 0.02093 -0.0220 0.0707 1.0000
9.250 1.0686 0.03261 0.02203 -0.0213 0.0686 1.0000
9.500 1.0904 0.03381 0.02343 -0.0207 0.0663 1.0000
9.750 1.1106 0.03499 0.02472 -0.0199 0.0641 1.0000
10.000 1.1295 0.03610 0.02586 -0.0191 0.0622 1.0000
10.250 1.1496 0.03738 0.02709 -0.0185 0.0607 1.0000
10.500 1.1680 0.03899 0.02900 -0.0175 0.0590 1.0000
10.750 1.1845 0.04060 0.03083 -0.0165 0.0574 1.0000
11.000 1.1986 0.04205 0.03243 -0.0151 0.0559 1.0000
11.250 1.2117 0.04340 0.03385 -0.0138 0.0547 1.0000
11.500 1.2263 0.04480 0.03527 -0.0128 0.0536 1.0000
11.750 1.2326 0.04701 0.03780 -0.0108 0.0526 1.0000
12.000 1.2354 0.04945 0.04058 -0.0088 0.0516 1.0000
12.250 1.2360 0.05191 0.04333 -0.0068 0.0507 1.0000
12.500 1.2354 0.05434 0.04600 -0.0050 0.0498 1.0000
12.750 1.2340 0.05677 0.04862 -0.0035 0.0490 1.0000
13.000 1.2329 0.05915 0.05117 -0.0022 0.0483 1.0000
13.250 1.2327 0.06152 0.05366 -0.0011 0.0476 1.0000
13.500 1.2338 0.06391 0.05612 -0.0003 0.0471 1.0000
13.750 1.2206 0.06779 0.06026 0.0004 0.0467 1.0000
14.000 1.1960 0.07306 0.06588 0.0005 0.0465 1.0000
14.250 1.1681 0.07916 0.07230 -0.0005 0.0463 1.0000
14.500 1.1358 0.08642 0.07987 -0.0029 0.0463 1.0000
14.750 1.0981 0.09539 0.08912 -0.0072 0.0464 1.0000
15.000 1.0513 0.10765 0.10165 -0.0146 0.0466 1.0000
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Polar data table (+)
Polar graphs
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