RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il) Reynolds number: 50,000 Max Cl/Cd: 31.87 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-amsoil1-il-50000-n5.txt Download as CSV file: xf-amsoil1-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4881 0.09652 0.08875 -0.0375 1.0000 0.0785
-9.250 -0.4858 0.09235 0.08462 -0.0393 1.0000 0.0779
-9.000 -0.4897 0.08740 0.07971 -0.0425 1.0000 0.0774
-8.750 -0.4996 0.08245 0.07481 -0.0456 1.0000 0.0770
-8.500 -0.5119 0.07793 0.07030 -0.0474 1.0000 0.0768
-8.250 -0.5240 0.07364 0.06598 -0.0482 1.0000 0.0768
-8.000 -0.5370 0.06987 0.06214 -0.0477 1.0000 0.0768
-7.750 -0.5502 0.06652 0.05870 -0.0459 1.0000 0.0769
-7.500 -0.5612 0.06336 0.05540 -0.0438 1.0000 0.0770
-7.250 -0.5691 0.06024 0.05210 -0.0415 1.0000 0.0771
-7.000 -0.5734 0.05711 0.04874 -0.0394 1.0000 0.0772
-6.750 -0.5742 0.05396 0.04530 -0.0375 1.0000 0.0774
-6.500 -0.5726 0.05066 0.04157 -0.0357 1.0000 0.0782
-6.250 -0.5653 0.04815 0.03880 -0.0342 1.0000 0.0796
-6.000 -0.5537 0.04659 0.03719 -0.0328 1.0000 0.0812
-5.750 -0.5261 0.04400 0.03427 -0.0346 0.9948 0.0833
-5.500 -0.4979 0.04122 0.03103 -0.0362 0.9893 0.0849
-5.250 -0.4671 0.03867 0.02790 -0.0380 0.9843 0.0882
-5.000 -0.4377 0.03674 0.02565 -0.0393 0.9790 0.0912
-4.750 -0.4062 0.03522 0.02397 -0.0408 0.9740 0.0940
-4.500 -0.3737 0.03377 0.02223 -0.0422 0.9693 0.0981
-4.250 -0.3428 0.03241 0.02051 -0.0431 0.9639 0.1027
-4.000 -0.3093 0.03133 0.01941 -0.0447 0.9595 0.1071
-3.750 -0.2777 0.03042 0.01829 -0.0456 0.9546 0.1133
-3.500 -0.2469 0.02955 0.01740 -0.0463 0.9492 0.1195
-3.250 -0.2122 0.02885 0.01660 -0.0476 0.9450 0.1280
-3.000 -0.1810 0.02820 0.01598 -0.0484 0.9403 0.1369
-2.750 -0.1515 0.02770 0.01540 -0.0488 0.9345 0.1483
-2.500 -0.1177 0.02716 0.01487 -0.0501 0.9300 0.1629
-2.250 -0.0862 0.02664 0.01441 -0.0512 0.9254 0.1806
-2.000 -0.0614 0.02617 0.01405 -0.0510 0.9189 0.2020
-1.750 -0.0300 0.02547 0.01363 -0.0523 0.9141 0.2407
-1.500 -0.0041 0.02353 0.01341 -0.0528 0.9107 0.4931
-1.250 0.0017 0.02343 0.01423 -0.0456 0.9035 0.8046
-1.000 0.0389 0.02374 0.01453 -0.0450 0.8997 0.9141
-0.750 0.1588 0.02397 0.01443 -0.0618 0.9042 1.0000
-0.500 0.1819 0.02411 0.01443 -0.0616 0.8971 1.0000
-0.250 0.2020 0.02430 0.01451 -0.0609 0.8897 1.0000
0.000 0.2190 0.02453 0.01464 -0.0596 0.8814 1.0000
0.250 0.2483 0.02471 0.01471 -0.0603 0.8762 1.0000
0.500 0.2564 0.02507 0.01500 -0.0574 0.8661 1.0000
0.750 0.2833 0.02530 0.01516 -0.0577 0.8602 1.0000
1.000 0.2989 0.02568 0.01548 -0.0560 0.8519 1.0000
1.250 0.3218 0.02602 0.01577 -0.0556 0.8448 1.0000
1.500 0.3537 0.02627 0.01599 -0.0565 0.8401 1.0000
1.750 0.3648 0.02683 0.01652 -0.0543 0.8302 1.0000
2.000 0.3942 0.02714 0.01683 -0.0547 0.8245 1.0000
2.250 0.4140 0.02764 0.01733 -0.0538 0.8165 1.0000
2.500 0.4383 0.02806 0.01778 -0.0535 0.8089 1.0000
2.750 0.4724 0.02829 0.01806 -0.0545 0.8039 1.0000
3.000 0.4859 0.02895 0.01876 -0.0527 0.7927 1.0000
3.250 0.5223 0.02899 0.01887 -0.0536 0.7863 1.0000
3.500 0.5479 0.02888 0.01885 -0.0524 0.7706 1.0000
3.750 0.5863 0.02763 0.01765 -0.0513 0.7489 1.0000
4.000 0.6119 0.02667 0.01675 -0.0486 0.7217 1.0000
4.250 0.6443 0.02553 0.01568 -0.0467 0.6986 1.0000
4.500 0.6653 0.02520 0.01543 -0.0444 0.6746 1.0000
4.750 0.6893 0.02465 0.01498 -0.0422 0.6478 1.0000
5.000 0.7095 0.02432 0.01473 -0.0398 0.6132 1.0000
5.250 0.7279 0.02408 0.01453 -0.0370 0.5632 1.0000
5.500 0.7514 0.02358 0.01360 -0.0340 0.4506 1.0000
5.750 0.7589 0.02482 0.01361 -0.0299 0.3039 1.0000
6.000 0.7640 0.02658 0.01477 -0.0271 0.2437 1.0000
6.250 0.7739 0.02809 0.01595 -0.0250 0.2113 1.0000
6.500 0.7861 0.02947 0.01709 -0.0232 0.1902 1.0000
6.750 0.8011 0.03071 0.01821 -0.0216 0.1737 1.0000
7.000 0.8191 0.03183 0.01927 -0.0204 0.1597 1.0000
7.250 0.8395 0.03292 0.02034 -0.0194 0.1481 1.0000
7.500 0.8625 0.03402 0.02138 -0.0187 0.1385 1.0000
7.750 0.8884 0.03508 0.02245 -0.0183 0.1295 1.0000
8.000 0.9182 0.03622 0.02365 -0.0183 0.1218 1.0000
8.250 0.9460 0.03742 0.02483 -0.0183 0.1152 1.0000
8.500 0.9754 0.03883 0.02633 -0.0184 0.1094 1.0000
8.750 1.0026 0.04031 0.02792 -0.0184 0.1045 1.0000
9.000 1.0297 0.04187 0.02936 -0.0186 0.1004 1.0000
9.250 1.0511 0.04373 0.03161 -0.0179 0.0964 1.0000
9.500 1.0727 0.04567 0.03376 -0.0173 0.0932 1.0000
9.750 1.0934 0.04748 0.03564 -0.0168 0.0903 1.0000
10.000 1.1109 0.04965 0.03799 -0.0161 0.0878 1.0000
10.250 1.1208 0.05224 0.04102 -0.0145 0.0853 1.0000
10.500 1.1301 0.05492 0.04403 -0.0130 0.0835 1.0000
10.750 1.1379 0.05750 0.04687 -0.0115 0.0818 1.0000
11.000 1.1464 0.05986 0.04939 -0.0102 0.0801 1.0000
11.250 1.1582 0.06213 0.05170 -0.0093 0.0785 1.0000
11.500 1.1450 0.06551 0.05547 -0.0064 0.0776 1.0000
11.750 1.1268 0.06912 0.05945 -0.0036 0.0769 1.0000
12.000 1.1060 0.07321 0.06386 -0.0017 0.0765 1.0000
12.250 1.0818 0.07792 0.06887 -0.0008 0.0763 1.0000
12.500 1.0538 0.08348 0.07469 -0.0010 0.0763 1.0000
12.750 1.0215 0.09022 0.08166 -0.0028 0.0764 1.0000
13.000 0.9850 0.09859 0.09022 -0.0065 0.0768 1.0000
13.250 0.9443 0.10936 0.10114 -0.0127 0.0773 1.0000
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Polar data table (+)
Polar graphs
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