DEFIANT CANARD BL145 AIRFOIL (defcnd3-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: DEFIANT CANARD BL145 AIRFOIL (defcnd3-il) Reynolds number: 1,000,000 Max Cl/Cd: 103.75 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-defcnd3-il-1000000.txt Download as CSV file: xf-defcnd3-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4669 0.08331 0.08164 -0.0270 1.0000 0.0117
-9.250 -0.4728 0.07882 0.07717 -0.0289 1.0000 0.0118
-9.000 -0.4840 0.07329 0.07167 -0.0318 1.0000 0.0119
-8.750 -0.4276 0.04886 0.04735 -0.0410 1.0000 0.0131
-8.500 -0.4643 0.04344 0.04188 -0.0448 1.0000 0.0124
-8.250 -0.5021 0.03982 0.03818 -0.0415 1.0000 0.0122
-8.000 -0.5201 0.03461 0.03283 -0.0408 0.9994 0.0123
-7.750 -0.5479 0.01821 0.01534 -0.0444 0.9938 0.0139
-7.500 -0.5220 0.01600 0.01308 -0.0460 0.9916 0.0141
-7.250 -0.4917 0.01455 0.01161 -0.0481 0.9899 0.0145
-7.000 -0.4679 0.01243 0.00929 -0.0489 0.9864 0.0148
-6.000 -0.4002 0.01479 0.00972 -0.0462 0.9764 0.0114
-5.750 -0.3687 0.01420 0.00902 -0.0467 0.9718 0.0112
-5.500 -0.3334 0.01349 0.00826 -0.0481 0.9675 0.0111
-5.250 -0.3132 0.01250 0.00722 -0.0463 0.9532 0.0112
-5.000 -0.2838 0.01165 0.00634 -0.0465 0.9404 0.0113
-4.750 -0.2406 0.01079 0.00544 -0.0497 0.9308 0.0113
-4.500 -0.1910 0.01004 0.00462 -0.0543 0.9106 0.0113
-4.250 -0.1539 0.00961 0.00403 -0.0561 0.8704 0.0113
-4.000 -0.1299 0.00934 0.00358 -0.0550 0.8310 0.0114
-3.750 -0.1072 0.00916 0.00323 -0.0537 0.7957 0.0115
-3.500 -0.0842 0.00898 0.00292 -0.0524 0.7643 0.0117
-3.250 -0.0608 0.00883 0.00265 -0.0513 0.7344 0.0121
-3.000 -0.0365 0.00871 0.00242 -0.0503 0.7094 0.0127
-2.750 -0.0117 0.00862 0.00222 -0.0494 0.6878 0.0133
-2.500 0.0134 0.00848 0.00201 -0.0486 0.6680 0.0147
-2.250 0.0389 0.00841 0.00185 -0.0479 0.6480 0.0162
-2.000 0.0639 0.00825 0.00169 -0.0471 0.6284 0.0297
-1.750 0.0861 0.00777 0.00152 -0.0460 0.6083 0.1317
-1.500 0.1065 0.00711 0.00136 -0.0447 0.5907 0.2977
-1.250 0.1282 0.00667 0.00132 -0.0435 0.5747 0.4381
-1.000 0.1525 0.00651 0.00129 -0.0426 0.5595 0.5011
-0.750 0.1773 0.00638 0.00128 -0.0419 0.5451 0.5539
-0.500 0.2019 0.00626 0.00128 -0.0410 0.5315 0.6093
-0.250 0.2252 0.00613 0.00131 -0.0399 0.5185 0.6825
0.000 0.2500 0.00611 0.00134 -0.0390 0.5047 0.7233
0.250 0.2747 0.00607 0.00135 -0.0381 0.4903 0.7597
0.500 0.2981 0.00597 0.00138 -0.0369 0.4776 0.8051
1.000 0.3479 0.00591 0.00148 -0.0350 0.4523 0.9007
1.250 0.3826 0.00596 0.00155 -0.0362 0.4385 0.9306
1.500 0.4230 0.00609 0.00162 -0.0389 0.4229 0.9522
1.750 0.4634 0.00624 0.00169 -0.0415 0.4059 0.9641
2.000 0.5010 0.00640 0.00177 -0.0435 0.3883 0.9731
2.250 0.5377 0.00658 0.00185 -0.0454 0.3700 0.9788
2.500 0.5705 0.00680 0.00195 -0.0464 0.3460 0.9855
2.750 0.6066 0.00707 0.00205 -0.0482 0.3135 0.9900
3.000 0.6404 0.00734 0.00218 -0.0496 0.2851 0.9942
3.250 0.6769 0.00757 0.00229 -0.0515 0.2653 0.9972
3.500 0.7141 0.00777 0.00241 -0.0536 0.2517 0.9997
3.750 0.7391 0.00791 0.00251 -0.0530 0.2445 1.0000
4.000 0.7615 0.00808 0.00263 -0.0518 0.2375 1.0000
4.250 0.7842 0.00823 0.00275 -0.0507 0.2316 1.0000
4.500 0.8075 0.00835 0.00287 -0.0497 0.2273 1.0000
4.750 0.8304 0.00852 0.00301 -0.0486 0.2217 1.0000
5.000 0.8532 0.00870 0.00315 -0.0476 0.2152 1.0000
5.250 0.8772 0.00880 0.00327 -0.0467 0.2114 1.0000
5.500 0.9008 0.00894 0.00340 -0.0458 0.2066 1.0000
5.750 0.9237 0.00914 0.00357 -0.0447 0.2006 1.0000
6.000 0.9479 0.00925 0.00370 -0.0439 0.1960 1.0000
6.250 0.9715 0.00941 0.00384 -0.0430 0.1890 1.0000
6.500 0.9949 0.00960 0.00400 -0.0421 0.1815 1.0000
6.750 1.0178 0.00981 0.00417 -0.0411 0.1711 1.0000
7.000 1.0402 0.01008 0.00437 -0.0401 0.1569 1.0000
7.250 1.0609 0.01046 0.00463 -0.0388 0.1348 1.0000
7.500 1.0788 0.01104 0.00504 -0.0370 0.1078 1.0000
7.750 1.0981 0.01153 0.00543 -0.0355 0.0922 1.0000
8.000 1.1182 0.01195 0.00580 -0.0341 0.0834 1.0000
8.250 1.1397 0.01227 0.00612 -0.0329 0.0782 1.0000
8.500 1.1597 0.01269 0.00651 -0.0316 0.0724 1.0000
8.750 1.1818 0.01297 0.00681 -0.0305 0.0695 1.0000
9.000 1.2023 0.01335 0.00718 -0.0293 0.0658 1.0000
9.250 1.2226 0.01374 0.00758 -0.0280 0.0623 1.0000
9.500 1.2440 0.01404 0.00791 -0.0269 0.0600 1.0000
9.750 1.2638 0.01445 0.00831 -0.0256 0.0571 1.0000
10.000 1.2822 0.01494 0.00881 -0.0240 0.0543 1.0000
10.250 1.3031 0.01524 0.00915 -0.0229 0.0528 1.0000
10.500 1.3226 0.01562 0.00955 -0.0216 0.0509 1.0000
10.750 1.3404 0.01610 0.01003 -0.0200 0.0487 1.0000
11.000 1.3573 0.01660 0.01055 -0.0183 0.0468 1.0000
11.250 1.3757 0.01698 0.01099 -0.0168 0.0460 1.0000
11.500 1.3919 0.01739 0.01144 -0.0150 0.0450 1.0000
11.750 1.4059 0.01785 0.01194 -0.0128 0.0440 1.0000
12.000 1.4191 0.01836 0.01247 -0.0105 0.0431 1.0000
12.250 1.4304 0.01898 0.01312 -0.0081 0.0420 1.0000
12.500 1.4385 0.01978 0.01397 -0.0053 0.0409 1.0000
12.750 1.4536 0.02025 0.01451 -0.0037 0.0404 1.0000
13.000 1.4679 0.02078 0.01509 -0.0020 0.0396 1.0000
13.250 1.4791 0.02150 0.01587 0.0000 0.0391 1.0000
13.500 1.4905 0.02224 0.01667 0.0018 0.0385 1.0000
13.750 1.5005 0.02309 0.01758 0.0035 0.0379 1.0000
14.000 1.5094 0.02408 0.01861 0.0052 0.0372 1.0000
14.250 1.5159 0.02528 0.01987 0.0068 0.0365 1.0000
14.500 1.5186 0.02689 0.02154 0.0084 0.0358 1.0000
14.750 1.5194 0.02880 0.02355 0.0096 0.0353 1.0000
15.000 1.5298 0.03006 0.02488 0.0102 0.0349 1.0000
15.250 1.5371 0.03167 0.02658 0.0107 0.0345 1.0000
15.500 1.5426 0.03354 0.02855 0.0110 0.0341 1.0000
15.750 1.5473 0.03561 0.03070 0.0110 0.0337 1.0000
16.000 1.5507 0.03790 0.03308 0.0109 0.0332 1.0000
16.250 1.5520 0.04052 0.03579 0.0105 0.0328 1.0000
16.500 1.5521 0.04336 0.03871 0.0100 0.0324 1.0000
16.750 1.5493 0.04659 0.04201 0.0092 0.0317 1.0000
17.000 1.5432 0.05034 0.04585 0.0082 0.0314 1.0000
17.250 1.5334 0.05458 0.05018 0.0070 0.0311 1.0000
17.500 1.5176 0.05970 0.05541 0.0053 0.0306 1.0000
17.750 1.5074 0.06420 0.06002 0.0039 0.0302 1.0000
18.000 1.4996 0.06844 0.06437 0.0024 0.0301 1.0000
18.250 1.4924 0.07270 0.06874 0.0009 0.0297 1.0000
18.500 1.4819 0.07748 0.07362 -0.0009 0.0295 1.0000
18.750 1.4766 0.08158 0.07781 -0.0024 0.0288 1.0000
19.000 1.4594 0.08742 0.08376 -0.0047 0.0288 1.0000
19.250 1.4499 0.09229 0.08872 -0.0067 0.0282 1.0000
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