DEFIANT CANARD BL145 AIRFOIL (defcnd3-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: DEFIANT CANARD BL145 AIRFOIL (defcnd3-il) Reynolds number: 50,000 Max Cl/Cd: 32.74 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-defcnd3-il-50000-n5.txt Download as CSV file: xf-defcnd3-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DEFIANT CANARD BL145 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4411 0.10938 0.10174 -0.0261 1.0000 0.0504
-10.000 -0.4365 0.10589 0.09829 -0.0264 1.0000 0.0500
-9.750 -0.4344 0.10219 0.09465 -0.0274 1.0000 0.0496
-9.500 -0.4330 0.09846 0.09099 -0.0284 1.0000 0.0490
-9.250 -0.4340 0.09440 0.08700 -0.0298 1.0000 0.0484
-9.000 -0.4369 0.09011 0.08279 -0.0315 1.0000 0.0476
-8.750 -0.4432 0.08531 0.07807 -0.0339 1.0000 0.0471
-8.500 -0.4830 0.07588 0.06863 -0.0412 1.0000 0.0433
-8.250 -0.4921 0.07212 0.06486 -0.0414 1.0000 0.0432
-8.000 -0.4982 0.06859 0.06131 -0.0411 1.0000 0.0429
-7.750 -0.5042 0.06497 0.05762 -0.0407 1.0000 0.0427
-7.500 -0.5084 0.06133 0.05385 -0.0399 1.0000 0.0425
-7.250 -0.5111 0.05760 0.04992 -0.0389 1.0000 0.0425
-7.000 -0.5093 0.05429 0.04641 -0.0377 1.0000 0.0423
-6.750 -0.5055 0.05096 0.04282 -0.0362 1.0000 0.0423
-6.500 -0.4992 0.04779 0.03933 -0.0346 1.0000 0.0422
-6.250 -0.4903 0.04479 0.03601 -0.0330 1.0000 0.0422
-6.000 -0.4792 0.04195 0.03282 -0.0312 1.0000 0.0422
-5.750 -0.4658 0.03938 0.02987 -0.0295 1.0000 0.0423
-5.500 -0.4505 0.03706 0.02720 -0.0278 1.0000 0.0425
-5.250 -0.4334 0.03490 0.02467 -0.0261 1.0000 0.0429
-5.000 -0.4152 0.03302 0.02251 -0.0244 1.0000 0.0435
-4.750 -0.3968 0.03149 0.02089 -0.0230 1.0000 0.0445
-4.500 -0.3782 0.03018 0.01949 -0.0215 1.0000 0.0462
-4.250 -0.3592 0.02901 0.01815 -0.0199 1.0000 0.0488
-4.000 -0.3408 0.02796 0.01703 -0.0183 1.0000 0.0519
-3.750 -0.3230 0.02708 0.01612 -0.0166 1.0000 0.0551
-3.500 -0.3051 0.02625 0.01512 -0.0148 1.0000 0.0584
-3.250 -0.2706 0.02531 0.01420 -0.0165 0.9920 0.0659
-3.000 -0.2288 0.02423 0.01316 -0.0196 0.9797 0.0834
-2.750 -0.1889 0.02267 0.01195 -0.0226 0.9671 0.1415
-2.500 -0.1645 0.02013 0.01150 -0.0229 0.9526 0.4943
-2.250 -0.1385 0.01953 0.01168 -0.0206 0.9373 0.6957
-2.000 -0.0995 0.01931 0.01163 -0.0204 0.9240 0.8100
-1.750 -0.0114 0.01952 0.01170 -0.0291 0.9206 0.9355
-1.500 0.0627 0.01940 0.01120 -0.0378 0.9089 0.9737
-1.250 0.1308 0.01916 0.01064 -0.0460 0.8958 1.0000
-1.000 0.1706 0.01891 0.01014 -0.0487 0.8755 1.0000
-0.750 0.2100 0.01869 0.00969 -0.0511 0.8552 1.0000
-0.500 0.2480 0.01853 0.00930 -0.0531 0.8348 1.0000
-0.250 0.2805 0.01845 0.00901 -0.0539 0.8119 1.0000
0.000 0.3107 0.01843 0.00878 -0.0541 0.7879 1.0000
0.250 0.3401 0.01843 0.00855 -0.0539 0.7634 1.0000
0.500 0.3653 0.01850 0.00840 -0.0530 0.7377 1.0000
0.750 0.3888 0.01862 0.00832 -0.0517 0.7128 1.0000
1.000 0.4125 0.01877 0.00827 -0.0505 0.6904 1.0000
1.250 0.4358 0.01897 0.00829 -0.0493 0.6704 1.0000
1.500 0.4587 0.01919 0.00837 -0.0481 0.6515 1.0000
1.750 0.4819 0.01944 0.00848 -0.0470 0.6327 1.0000
2.000 0.5050 0.01970 0.00862 -0.0459 0.6144 1.0000
2.250 0.5280 0.01998 0.00880 -0.0447 0.5963 1.0000
2.500 0.5508 0.02027 0.00899 -0.0436 0.5782 1.0000
2.750 0.5737 0.02058 0.00921 -0.0424 0.5603 1.0000
3.000 0.5965 0.02091 0.00948 -0.0413 0.5426 1.0000
3.250 0.6193 0.02125 0.00975 -0.0402 0.5250 1.0000
3.500 0.6420 0.02162 0.01006 -0.0391 0.5075 1.0000
3.750 0.6647 0.02201 0.01040 -0.0380 0.4903 1.0000
4.000 0.6873 0.02243 0.01080 -0.0369 0.4736 1.0000
4.250 0.7099 0.02288 0.01122 -0.0358 0.4576 1.0000
4.500 0.7325 0.02335 0.01167 -0.0348 0.4423 1.0000
4.750 0.7552 0.02385 0.01214 -0.0338 0.4278 1.0000
5.000 0.7784 0.02436 0.01262 -0.0329 0.4149 1.0000
5.250 0.8010 0.02491 0.01318 -0.0319 0.4020 1.0000
5.500 0.8230 0.02553 0.01385 -0.0310 0.3895 1.0000
5.750 0.8458 0.02612 0.01444 -0.0301 0.3785 1.0000
6.000 0.8683 0.02674 0.01511 -0.0291 0.3677 1.0000
6.250 0.8892 0.02742 0.01588 -0.0281 0.3562 1.0000
6.500 0.9102 0.02798 0.01644 -0.0269 0.3442 1.0000
6.750 0.9304 0.02843 0.01687 -0.0255 0.3309 1.0000
7.000 0.9481 0.02896 0.01746 -0.0240 0.3162 1.0000
7.250 0.9654 0.02956 0.01813 -0.0224 0.3021 1.0000
7.500 0.9829 0.03020 0.01886 -0.0209 0.2891 1.0000
7.750 1.0006 0.03086 0.01956 -0.0194 0.2767 1.0000
8.000 1.0184 0.03150 0.02018 -0.0179 0.2646 1.0000
8.250 1.0337 0.03229 0.02107 -0.0162 0.2515 1.0000
8.500 1.0479 0.03319 0.02210 -0.0145 0.2384 1.0000
8.750 1.0615 0.03415 0.02314 -0.0127 0.2254 1.0000
9.000 1.0742 0.03513 0.02414 -0.0109 0.2125 1.0000
9.250 1.0860 0.03617 0.02521 -0.0090 0.2001 1.0000
9.500 1.0939 0.03746 0.02669 -0.0068 0.1872 1.0000
9.750 1.1011 0.03878 0.02814 -0.0046 0.1758 1.0000
10.000 1.1082 0.04007 0.02946 -0.0025 0.1663 1.0000
10.250 1.1133 0.04141 0.03088 -0.0002 0.1581 1.0000
10.500 1.1166 0.04305 0.03264 0.0020 0.1506 1.0000
10.750 1.1209 0.04453 0.03413 0.0039 0.1443 1.0000
11.000 1.1234 0.04652 0.03624 0.0056 0.1387 1.0000
11.250 1.1253 0.04852 0.03836 0.0071 0.1336 1.0000
11.500 1.1316 0.05018 0.03995 0.0083 0.1294 1.0000
11.750 1.1265 0.05323 0.04329 0.0091 0.1253 1.0000
12.000 1.1244 0.05604 0.04626 0.0097 0.1219 1.0000
12.250 1.1287 0.05824 0.04850 0.0102 0.1188 1.0000
12.500 1.1266 0.06135 0.05172 0.0103 0.1160 1.0000
12.750 1.1098 0.06637 0.05703 0.0093 0.1141 1.0000
13.000 1.0880 0.07245 0.06336 0.0072 0.1123 1.0000
13.250 1.0579 0.08034 0.07149 0.0036 0.1110 1.0000
13.500 0.9667 0.10097 0.09240 -0.0084 0.1113 1.0000
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Polar data table (+)
Polar graphs
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