DEFIANT CANARD BL20 AIRFOIL (defcnd1-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: DEFIANT CANARD BL20 AIRFOIL (defcnd1-il) Reynolds number: 100,000 Max Cl/Cd: 32.28 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-defcnd1-il-100000-n5.txt Download as CSV file: xf-defcnd1-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DEFIANT CANARD BL20 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.5138 0.06500 0.05845 -0.0963 0.7783 0.0645
-13.750 -0.5272 0.06010 0.05340 -0.0996 0.7683 0.0660
-13.500 -0.5382 0.05580 0.04897 -0.1024 0.7593 0.0675
-13.250 -0.5546 0.05110 0.04405 -0.1053 0.7514 0.0694
-13.000 -0.5706 0.04672 0.03938 -0.1077 0.7447 0.0715
-12.750 -0.5708 0.04451 0.03715 -0.1087 0.7368 0.0734
-12.500 -0.5753 0.04206 0.03455 -0.1095 0.7299 0.0758
-12.250 -0.5815 0.03960 0.03182 -0.1096 0.7241 0.0786
-12.000 -0.5790 0.03831 0.03054 -0.1091 0.7176 0.0809
-11.750 -0.5799 0.03686 0.02892 -0.1080 0.7116 0.0840
-11.500 -0.5792 0.03565 0.02754 -0.1063 0.7063 0.0871
-11.250 -0.5751 0.03486 0.02669 -0.1044 0.7006 0.0901
-11.000 -0.5753 0.03381 0.02541 -0.1017 0.6949 0.0939
-10.750 -0.5690 0.03340 0.02497 -0.0993 0.6897 0.0967
-10.500 -0.5617 0.03289 0.02428 -0.0970 0.6855 0.1005
-10.250 -0.5530 0.03224 0.02348 -0.0949 0.6806 0.1047
-10.000 -0.5397 0.03188 0.02309 -0.0932 0.6754 0.1084
-9.750 -0.5297 0.03123 0.02214 -0.0911 0.6707 0.1133
-9.500 -0.5119 0.03087 0.02179 -0.0898 0.6665 0.1170
-9.250 -0.4963 0.03041 0.02119 -0.0883 0.6622 0.1215
-9.000 -0.4804 0.02984 0.02047 -0.0869 0.6574 0.1259
-8.750 -0.4606 0.02943 0.02007 -0.0859 0.6530 0.1298
-8.500 -0.4421 0.02894 0.01941 -0.0846 0.6489 0.1344
-8.250 -0.4222 0.02840 0.01870 -0.0835 0.6454 0.1385
-8.000 -0.4008 0.02798 0.01829 -0.0827 0.6413 0.1424
-7.750 -0.3805 0.02754 0.01778 -0.0817 0.6365 0.1467
-7.500 -0.3596 0.02708 0.01716 -0.0807 0.6323 0.1510
-7.250 -0.3369 0.02663 0.01673 -0.0799 0.6286 0.1548
-7.000 -0.3142 0.02623 0.01625 -0.0791 0.6254 0.1592
-6.750 -0.2915 0.02587 0.01571 -0.0783 0.6221 0.1637
-6.500 -0.2696 0.02547 0.01538 -0.0775 0.6175 0.1676
-6.250 -0.2473 0.02514 0.01506 -0.0766 0.6132 0.1720
-6.000 -0.2243 0.02482 0.01464 -0.0758 0.6095 0.1770
-5.750 -0.2007 0.02447 0.01423 -0.0751 0.6064 0.1817
-5.500 -0.1773 0.02413 0.01387 -0.0743 0.6036 0.1867
-5.250 -0.1551 0.02392 0.01364 -0.0735 0.5998 0.1925
-5.000 -0.1333 0.02369 0.01343 -0.0725 0.5954 0.1982
-4.750 -0.1114 0.02342 0.01320 -0.0715 0.5915 0.2047
-4.500 -0.0878 0.02319 0.01290 -0.0707 0.5882 0.2129
-4.250 -0.0651 0.02290 0.01265 -0.0698 0.5854 0.2219
-4.000 -0.0409 0.02265 0.01236 -0.0691 0.5830 0.2334
-3.750 -0.0209 0.02256 0.01238 -0.0679 0.5786 0.2476
-3.500 -0.0001 0.02243 0.01236 -0.0668 0.5744 0.2659
-3.250 0.0217 0.02227 0.01230 -0.0658 0.5708 0.2892
-3.000 0.0447 0.02214 0.01223 -0.0649 0.5678 0.3163
-2.750 0.0693 0.02205 0.01213 -0.0642 0.5653 0.3442
-2.500 0.0939 0.02202 0.01210 -0.0634 0.5628 0.3691
-2.250 0.1132 0.02222 0.01241 -0.0621 0.5582 0.3902
-2.000 0.1351 0.02234 0.01255 -0.0611 0.5541 0.4098
-1.750 0.1589 0.02240 0.01257 -0.0603 0.5507 0.4281
-1.500 0.1839 0.02241 0.01255 -0.0596 0.5479 0.4455
-1.250 0.2101 0.02238 0.01247 -0.0591 0.5455 0.4615
-1.000 0.2342 0.02247 0.01255 -0.0584 0.5426 0.4764
-0.500 0.2746 0.02289 0.01308 -0.0560 0.5339 0.5048
-0.250 0.2989 0.02292 0.01312 -0.0553 0.5308 0.5200
0.000 0.3243 0.02289 0.01310 -0.0547 0.5283 0.5402
0.250 0.3513 0.02277 0.01301 -0.0542 0.5261 0.5640
0.500 0.3699 0.02302 0.01339 -0.0528 0.5221 0.5852
0.750 0.3873 0.02332 0.01384 -0.0513 0.5175 0.6051
1.000 0.4101 0.02344 0.01403 -0.0504 0.5140 0.6265
1.250 0.4365 0.02343 0.01408 -0.0501 0.5112 0.6500
1.500 0.4659 0.02331 0.01401 -0.0501 0.5088 0.6784
1.750 0.4973 0.02314 0.01390 -0.0503 0.5067 0.7154
2.000 0.5085 0.02384 0.01490 -0.0480 0.5011 0.7592
2.250 0.5410 0.02416 0.01542 -0.0490 0.4969 0.8187
2.500 0.5948 0.02432 0.01562 -0.0537 0.4936 0.8767
2.750 0.6510 0.02434 0.01556 -0.0588 0.4909 0.9192
3.000 0.7040 0.02431 0.01538 -0.0633 0.4887 0.9486
3.250 0.7331 0.02535 0.01654 -0.0651 0.4830 0.9777
3.500 0.7754 0.02585 0.01702 -0.0687 0.4786 0.9987
3.750 0.7935 0.02605 0.01715 -0.0674 0.4755 1.0000
4.000 0.8145 0.02608 0.01706 -0.0662 0.4730 1.0000
4.250 0.8399 0.02602 0.01687 -0.0656 0.4710 1.0000
4.500 0.8244 0.02737 0.01834 -0.0597 0.4655 1.0000
4.750 0.8223 0.02822 0.01921 -0.0556 0.4609 1.0000
5.000 0.8369 0.02850 0.01944 -0.0536 0.4577 1.0000
5.250 0.8618 0.02847 0.01931 -0.0529 0.4554 1.0000
5.500 0.8927 0.02831 0.01905 -0.0531 0.4535 1.0000
5.750 0.8049 0.03205 0.02301 -0.0388 0.4442 1.0000
6.000 0.8127 0.03277 0.02370 -0.0366 0.4405 1.0000
6.250 0.8412 0.03258 0.02343 -0.0363 0.4384 1.0000
6.500 0.8784 0.03205 0.02281 -0.0369 0.4368 1.0000
7.000 0.7656 0.04263 0.03360 -0.0266 0.4155 1.0000
7.250 0.8173 0.04035 0.03122 -0.0269 0.4170 1.0000
7.500 0.8737 0.03796 0.02873 -0.0276 0.4183 1.0000
8.000 0.8224 0.04604 0.03691 -0.0233 0.4012 1.0000
10.000 0.8056 0.06742 0.05843 -0.0177 0.3524 1.0000
10.500 0.7883 0.07509 0.06617 -0.0174 0.3372 1.0000
10.750 0.8127 0.07490 0.06597 -0.0169 0.3363 1.0000
12.250 0.7716 0.09886 0.09018 -0.0185 0.2954 1.0000
12.750 0.8039 0.10078 0.09214 -0.0181 0.2910 1.0000
13.750 0.8280 0.11051 0.10200 -0.0192 0.2750 1.0000
14.000 0.8008 0.11805 0.10962 -0.0210 0.2651 1.0000
14.250 0.8147 0.11933 0.11093 -0.0211 0.2624 1.0000
|
Polar data table (+)
Polar graphs
<< Back to DEFIANT CANARD BL20 AIRFOIL (defcnd1-il)