DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Reynolds number: 500,000 Max Cl/Cd: 89.64 at α=8.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-defcnd2-il-500000-n5.txt Download as CSV file: xf-defcnd2-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: DEFIANT CANARD BL110 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4786 0.04029 0.03723 -0.1079 0.9040 0.0097
-11.000 -0.4942 0.03674 0.03332 -0.1079 0.8733 0.0098
-10.750 -0.5079 0.03454 0.03086 -0.1048 0.8535 0.0099
-10.500 -0.5194 0.03270 0.02877 -0.1007 0.8390 0.0099
-10.250 -0.5307 0.03064 0.02643 -0.0962 0.8279 0.0101
-10.000 -0.5266 0.02925 0.02482 -0.0936 0.8186 0.0102
-9.750 -0.5195 0.02788 0.02323 -0.0912 0.8113 0.0104
-9.500 -0.5132 0.02615 0.02121 -0.0886 0.8036 0.0107
-9.250 -0.5024 0.02470 0.01950 -0.0865 0.7968 0.0109
-9.000 -0.4894 0.02333 0.01786 -0.0846 0.7897 0.0112
-8.750 -0.4742 0.02205 0.01633 -0.0829 0.7845 0.0114
-8.500 -0.4566 0.02095 0.01502 -0.0815 0.7795 0.0116
-8.250 -0.4371 0.02010 0.01397 -0.0803 0.7742 0.0118
-8.000 -0.4167 0.01930 0.01299 -0.0791 0.7691 0.0119
-7.750 -0.3978 0.01812 0.01168 -0.0779 0.7636 0.0122
-7.500 -0.3766 0.01739 0.01086 -0.0770 0.7580 0.0125
-7.250 -0.3543 0.01682 0.01022 -0.0761 0.7530 0.0128
-7.000 -0.3316 0.01625 0.00958 -0.0753 0.7473 0.0131
-6.750 -0.3087 0.01574 0.00898 -0.0745 0.7415 0.0134
-6.500 -0.2856 0.01522 0.00838 -0.0737 0.7346 0.0138
-6.250 -0.2625 0.01474 0.00781 -0.0729 0.7269 0.0142
-6.000 -0.2387 0.01432 0.00732 -0.0722 0.7191 0.0147
-5.750 -0.2148 0.01399 0.00690 -0.0714 0.7100 0.0153
-5.500 -0.1918 0.01353 0.00636 -0.0705 0.6994 0.0157
-5.250 -0.1698 0.01301 0.00578 -0.0695 0.6882 0.0163
-5.000 -0.1468 0.01266 0.00535 -0.0686 0.6741 0.0169
-4.750 -0.1242 0.01240 0.00498 -0.0675 0.6529 0.0174
-4.500 -0.1018 0.01219 0.00462 -0.0665 0.6285 0.0181
-4.250 -0.0793 0.01203 0.00432 -0.0654 0.6040 0.0188
-4.000 -0.0564 0.01190 0.00405 -0.0644 0.5810 0.0196
-3.750 -0.0335 0.01174 0.00378 -0.0635 0.5629 0.0207
-3.500 -0.0099 0.01159 0.00354 -0.0627 0.5497 0.0224
-3.250 0.0146 0.01146 0.00334 -0.0620 0.5399 0.0240
-2.750 0.0638 0.01120 0.00300 -0.0607 0.5235 0.0312
-2.500 0.0876 0.01102 0.00286 -0.0600 0.5161 0.0504
-2.250 0.1119 0.01082 0.00274 -0.0594 0.5090 0.0777
-2.000 0.1359 0.01065 0.00264 -0.0587 0.5015 0.1085
-1.750 0.1598 0.01043 0.00254 -0.0580 0.4946 0.1541
-1.250 0.2049 0.00987 0.00238 -0.0563 0.4774 0.2961
-1.000 0.2233 0.00936 0.00229 -0.0548 0.4671 0.4345
-0.750 0.2413 0.00894 0.00225 -0.0529 0.4556 0.5606
-0.500 0.2601 0.00871 0.00231 -0.0510 0.4441 0.6704
-0.250 0.2825 0.00867 0.00233 -0.0499 0.4319 0.7137
0.000 0.3058 0.00869 0.00236 -0.0489 0.4190 0.7421
0.250 0.3294 0.00874 0.00239 -0.0480 0.4072 0.7660
0.500 0.3528 0.00878 0.00244 -0.0470 0.3971 0.7898
0.750 0.3759 0.00879 0.00251 -0.0459 0.3900 0.8237
1.000 0.3999 0.00883 0.00260 -0.0450 0.3840 0.8578
1.250 0.4263 0.00890 0.00268 -0.0447 0.3794 0.8804
1.500 0.4547 0.00899 0.00276 -0.0448 0.3757 0.8964
1.750 0.4844 0.00910 0.00286 -0.0453 0.3717 0.9106
2.000 0.5155 0.00925 0.00296 -0.0461 0.3679 0.9236
2.250 0.5497 0.00940 0.00308 -0.0476 0.3649 0.9339
2.500 0.5848 0.00953 0.00319 -0.0493 0.3626 0.9425
2.750 0.6194 0.00967 0.00330 -0.0509 0.3603 0.9507
3.000 0.6545 0.00982 0.00343 -0.0527 0.3580 0.9570
3.250 0.6895 0.00999 0.00356 -0.0545 0.3553 0.9625
3.500 0.7213 0.01017 0.00371 -0.0556 0.3525 0.9692
3.750 0.7558 0.01035 0.00386 -0.0573 0.3503 0.9735
4.000 0.7879 0.01048 0.00400 -0.0584 0.3487 0.9793
4.250 0.8203 0.01062 0.00414 -0.0596 0.3468 0.9839
4.500 0.8540 0.01077 0.00429 -0.0611 0.3449 0.9879
4.750 0.8863 0.01093 0.00446 -0.0624 0.3427 0.9923
5.000 0.9193 0.01111 0.00463 -0.0638 0.3405 0.9962
5.250 0.9528 0.01131 0.00481 -0.0654 0.3383 0.9993
5.500 0.9752 0.01150 0.00500 -0.0647 0.3360 1.0000
5.750 0.9943 0.01162 0.00515 -0.0631 0.3342 1.0000
6.000 1.0140 0.01174 0.00529 -0.0617 0.3324 1.0000
6.250 1.0336 0.01187 0.00546 -0.0602 0.3304 1.0000
6.500 1.0530 0.01201 0.00564 -0.0587 0.3282 1.0000
6.750 1.0721 0.01217 0.00582 -0.0572 0.3260 1.0000
7.000 1.0908 0.01236 0.00602 -0.0556 0.3237 1.0000
7.250 1.1089 0.01257 0.00624 -0.0540 0.3215 1.0000
7.500 1.1281 0.01275 0.00646 -0.0525 0.3194 1.0000
7.750 1.1478 0.01289 0.00666 -0.0511 0.3169 1.0000
8.000 1.1655 0.01304 0.00687 -0.0494 0.3141 1.0000
8.250 1.1817 0.01320 0.00707 -0.0473 0.3097 1.0000
8.500 1.1974 0.01338 0.00728 -0.0452 0.3040 1.0000
8.750 1.2137 0.01354 0.00745 -0.0433 0.2914 1.0000
9.000 1.2286 0.01380 0.00768 -0.0413 0.2783 1.0000
9.250 1.2386 0.01427 0.00805 -0.0385 0.2623 1.0000
9.500 1.2514 0.01473 0.00850 -0.0364 0.2545 1.0000
9.750 1.2642 0.01524 0.00899 -0.0343 0.2466 1.0000
10.000 1.2748 0.01587 0.00960 -0.0320 0.2384 1.0000
10.250 1.2903 0.01633 0.01010 -0.0305 0.2327 1.0000
10.500 1.3019 0.01700 0.01077 -0.0286 0.2246 1.0000
10.750 1.3161 0.01758 0.01138 -0.0271 0.2146 1.0000
11.000 1.3245 0.01849 0.01221 -0.0251 0.1863 1.0000
11.250 1.3116 0.02073 0.01411 -0.0210 0.1390 1.0000
11.500 1.3114 0.02236 0.01567 -0.0186 0.1193 1.0000
11.750 1.3067 0.02439 0.01759 -0.0160 0.0967 1.0000
12.000 1.3122 0.02582 0.01902 -0.0145 0.0880 1.0000
12.250 1.3089 0.02795 0.02109 -0.0126 0.0712 1.0000
12.500 1.3134 0.02959 0.02275 -0.0114 0.0646 1.0000
12.750 1.3071 0.03216 0.02527 -0.0097 0.0495 1.0000
13.000 1.3006 0.03491 0.02799 -0.0084 0.0375 1.0000
13.250 1.2930 0.03793 0.03100 -0.0074 0.0270 1.0000
13.500 1.2848 0.04122 0.03430 -0.0067 0.0191 1.0000
13.750 1.2790 0.04445 0.03757 -0.0063 0.0138 1.0000
14.000 1.2740 0.04774 0.04091 -0.0062 0.0099 1.0000
14.250 1.2700 0.05102 0.04426 -0.0062 0.0080 1.0000
14.500 1.2634 0.05473 0.04804 -0.0064 0.0063 1.0000
14.750 1.2621 0.05782 0.05122 -0.0066 0.0061 1.0000
15.000 1.2591 0.06117 0.05466 -0.0069 0.0058 1.0000
15.250 1.2546 0.06478 0.05835 -0.0073 0.0054 1.0000
15.500 1.2464 0.06886 0.06254 -0.0078 0.0049 1.0000
15.750 1.2436 0.07231 0.06607 -0.0083 0.0049 1.0000
16.000 1.2385 0.07613 0.06998 -0.0090 0.0047 1.0000
16.250 1.2343 0.07989 0.07383 -0.0097 0.0047 1.0000
16.500 1.2302 0.08364 0.07767 -0.0104 0.0045 1.0000
16.750 1.2262 0.08744 0.08156 -0.0112 0.0045 1.0000
17.000 1.2227 0.09120 0.08541 -0.0120 0.0044 1.0000
17.250 1.2191 0.09500 0.08929 -0.0129 0.0043 1.0000
17.500 1.2151 0.09887 0.09325 -0.0139 0.0042 1.0000
17.750 1.2109 0.10279 0.09726 -0.0149 0.0041 1.0000
18.000 1.2089 0.10639 0.10094 -0.0159 0.0041 1.0000
18.250 1.2038 0.11052 0.10515 -0.0171 0.0040 1.0000
18.500 1.2007 0.11436 0.10907 -0.0183 0.0039 1.0000
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Polar data table (+)
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