RUTAN CANARD AIRFOIL (amsoil1-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: RUTAN CANARD AIRFOIL (amsoil1-il) Reynolds number: 200,000 Max Cl/Cd: 67.46 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-amsoil1-il-200000.txt Download as CSV file: xf-amsoil1-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5047 0.08354 0.07987 -0.0451 1.0000 0.0783
-8.750 -0.5585 0.07745 0.07356 -0.0509 1.0000 0.0788
-8.500 -0.5601 0.07360 0.06984 -0.0483 1.0000 0.0794
-8.250 -0.5657 0.07211 0.06843 -0.0441 1.0000 0.0798
-8.000 -0.5601 0.07020 0.06657 -0.0423 0.9987 0.0805
-7.750 -0.5363 0.06713 0.06349 -0.0447 0.9949 0.0820
-7.500 -0.5170 0.06289 0.05913 -0.0491 0.9894 0.0849
-7.250 -0.5064 0.05499 0.05071 -0.0570 0.9827 0.0912
-7.000 -0.5045 0.04038 0.03491 -0.0604 0.9744 0.0703
-6.750 -0.4731 0.03636 0.03071 -0.0629 0.9720 0.0665
-6.500 -0.4505 0.03195 0.02576 -0.0638 0.9658 0.0657
-6.250 -0.4214 0.02863 0.02195 -0.0651 0.9615 0.0659
-6.000 -0.3887 0.02598 0.01886 -0.0667 0.9584 0.0666
-5.750 -0.3618 0.02437 0.01688 -0.0667 0.9520 0.0683
-5.500 -0.3310 0.02279 0.01496 -0.0675 0.9472 0.0701
-5.250 -0.2986 0.02156 0.01372 -0.0686 0.9436 0.0719
-5.000 -0.2726 0.02083 0.01293 -0.0684 0.9369 0.0739
-4.750 -0.2434 0.02012 0.01209 -0.0685 0.9316 0.0769
-4.500 -0.2138 0.01924 0.01105 -0.0687 0.9275 0.0797
-4.250 -0.1891 0.01856 0.01044 -0.0682 0.9203 0.0824
-4.000 -0.1618 0.01807 0.00992 -0.0679 0.9149 0.0862
-3.750 -0.1343 0.01752 0.00928 -0.0675 0.9107 0.0906
-3.500 -0.1096 0.01702 0.00889 -0.0671 0.9036 0.0954
-3.250 -0.0829 0.01669 0.00850 -0.0667 0.8982 0.1012
-3.000 -0.0574 0.01613 0.00804 -0.0660 0.8940 0.1086
-2.750 -0.0318 0.01582 0.00774 -0.0657 0.8873 0.1171
-2.500 -0.0060 0.01547 0.00747 -0.0653 0.8818 0.1276
-2.250 0.0199 0.01509 0.00716 -0.0647 0.8776 0.1405
-2.000 0.0457 0.01479 0.00697 -0.0644 0.8722 0.1570
-1.750 0.0716 0.01449 0.00677 -0.0642 0.8660 0.1815
-1.500 0.0967 0.01388 0.00650 -0.0637 0.8614 0.2397
-1.250 0.1080 0.01208 0.00668 -0.0604 0.8574 0.7300
-1.000 0.1270 0.01222 0.00705 -0.0577 0.8504 0.8142
-0.750 0.1472 0.01234 0.00720 -0.0550 0.8450 0.8561
-0.500 0.1670 0.01242 0.00729 -0.0520 0.8410 0.8848
-0.250 0.1872 0.01261 0.00748 -0.0498 0.8348 0.9101
0.000 0.2107 0.01270 0.00757 -0.0480 0.8291 0.9312
0.250 0.2422 0.01274 0.00757 -0.0478 0.8251 0.9503
0.500 0.2842 0.01279 0.00757 -0.0500 0.8223 0.9661
0.750 0.3382 0.01295 0.00772 -0.0552 0.8177 0.9780
1.000 0.3996 0.01300 0.00777 -0.0619 0.8135 0.9905
1.250 0.4516 0.01274 0.00746 -0.0663 0.8069 1.0000
1.500 0.4712 0.01249 0.00718 -0.0645 0.7947 1.0000
1.750 0.4911 0.01213 0.00673 -0.0624 0.7844 1.0000
2.000 0.5117 0.01194 0.00654 -0.0609 0.7727 1.0000
2.250 0.5324 0.01176 0.00632 -0.0593 0.7618 1.0000
2.500 0.5535 0.01149 0.00597 -0.0576 0.7508 1.0000
2.750 0.5739 0.01132 0.00580 -0.0559 0.7367 1.0000
3.000 0.5950 0.01119 0.00566 -0.0544 0.7237 1.0000
3.250 0.6171 0.01106 0.00549 -0.0530 0.7112 1.0000
3.500 0.6402 0.01094 0.00533 -0.0517 0.6971 1.0000
3.750 0.6639 0.01086 0.00525 -0.0507 0.6788 1.0000
4.000 0.6883 0.01081 0.00519 -0.0497 0.6548 1.0000
4.250 0.7128 0.01080 0.00509 -0.0487 0.6228 1.0000
4.500 0.7360 0.01091 0.00502 -0.0474 0.5670 1.0000
4.750 0.7495 0.01187 0.00513 -0.0447 0.4086 1.0000
5.000 0.7546 0.01398 0.00612 -0.0418 0.2259 1.0000
5.250 0.7713 0.01511 0.00687 -0.0404 0.1759 1.0000
5.500 0.7912 0.01594 0.00753 -0.0393 0.1521 1.0000
5.750 0.8117 0.01670 0.00818 -0.0383 0.1365 1.0000
6.000 0.8318 0.01750 0.00886 -0.0373 0.1249 1.0000
6.250 0.8529 0.01819 0.00949 -0.0364 0.1154 1.0000
6.500 0.8740 0.01893 0.01021 -0.0354 0.1077 1.0000
6.750 0.8941 0.01980 0.01097 -0.0344 0.1013 1.0000
7.000 0.9162 0.02052 0.01173 -0.0335 0.0959 1.0000
7.250 0.9378 0.02126 0.01240 -0.0327 0.0911 1.0000
7.500 0.9598 0.02227 0.01337 -0.0320 0.0871 1.0000
7.750 0.9828 0.02301 0.01417 -0.0313 0.0835 1.0000
8.000 1.0057 0.02383 0.01493 -0.0307 0.0803 1.0000
8.250 1.0301 0.02502 0.01609 -0.0304 0.0773 1.0000
8.500 1.0536 0.02586 0.01705 -0.0298 0.0747 1.0000
8.750 1.0772 0.02678 0.01800 -0.0293 0.0724 1.0000
9.000 1.1017 0.02782 0.01897 -0.0290 0.0702 1.0000
9.250 1.1267 0.02926 0.02048 -0.0289 0.0681 1.0000
9.500 1.1487 0.03037 0.02178 -0.0281 0.0662 1.0000
9.750 1.1713 0.03158 0.02311 -0.0275 0.0645 1.0000
10.000 1.1930 0.03271 0.02428 -0.0269 0.0629 1.0000
10.250 1.2179 0.03429 0.02580 -0.0270 0.0612 1.0000
10.500 1.2352 0.03607 0.02786 -0.0258 0.0599 1.0000
10.750 1.2503 0.03787 0.02997 -0.0243 0.0587 1.0000
11.000 1.2645 0.03975 0.03211 -0.0229 0.0575 1.0000
11.250 1.2789 0.04140 0.03393 -0.0215 0.0562 1.0000
11.500 1.2968 0.04268 0.03522 -0.0207 0.0550 1.0000
11.750 1.3147 0.04448 0.03701 -0.0202 0.0539 1.0000
12.000 1.3202 0.04756 0.04038 -0.0183 0.0532 1.0000
12.250 1.3143 0.05030 0.04352 -0.0149 0.0527 1.0000
12.500 1.3014 0.05316 0.04674 -0.0109 0.0524 1.0000
12.750 1.2846 0.05640 0.05031 -0.0073 0.0521 1.0000
13.000 1.2646 0.06011 0.05433 -0.0044 0.0519 1.0000
13.250 1.2412 0.06434 0.05886 -0.0022 0.0517 1.0000
13.500 1.2146 0.06923 0.06402 -0.0010 0.0517 1.0000
13.750 1.1850 0.07486 0.06991 -0.0008 0.0519 1.0000
14.000 1.1530 0.08137 0.07666 -0.0019 0.0521 1.0000
14.250 1.1195 0.08883 0.08432 -0.0044 0.0524 1.0000
14.500 1.0864 0.09718 0.09284 -0.0082 0.0528 1.0000
14.750 1.0576 0.10597 0.10175 -0.0127 0.0532 1.0000
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Polar data table (+)
Polar graphs
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