DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
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Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.18 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-defcnd2-il-1000000.txt Download as CSV file: xf-defcnd2-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2972 0.11266 0.11108 -0.0452 0.9756 0.0133
-11.500 -0.2785 0.10695 0.10533 -0.0523 0.9604 0.0143
-11.250 -0.3460 0.03515 0.03303 -0.1030 0.8971 0.0121
-11.000 -0.3776 0.02971 0.02731 -0.1060 0.8707 0.0121
-10.750 -0.4108 0.02593 0.02328 -0.1057 0.8516 0.0121
-10.500 -0.4355 0.02351 0.02065 -0.1033 0.8382 0.0122
-10.250 -0.4415 0.02260 0.01958 -0.1005 0.8279 0.0120
-10.000 -0.4608 0.02083 0.01762 -0.0956 0.8186 0.0120
-9.750 -0.4755 0.01856 0.01512 -0.0911 0.8115 0.0121
-9.500 -0.4728 0.01708 0.01345 -0.0884 0.8055 0.0120
-9.250 -0.4743 0.01483 0.01092 -0.0853 0.8002 0.0120
-9.000 -0.4707 0.01273 0.00857 -0.0827 0.7952 0.0120
-8.750 -0.4684 0.02234 0.01769 -0.0843 0.7972 0.0120
-8.500 -0.4584 0.01996 0.01502 -0.0820 0.7922 0.0122
-8.250 -0.4414 0.01864 0.01356 -0.0806 0.7874 0.0125
-8.000 -0.4217 0.01758 0.01236 -0.0794 0.7830 0.0126
-7.750 -0.3995 0.01708 0.01181 -0.0786 0.7782 0.0130
-7.500 -0.3773 0.01648 0.01112 -0.0777 0.7734 0.0133
-7.250 -0.3539 0.01606 0.01064 -0.0771 0.7687 0.0138
-7.000 -0.3314 0.01528 0.00975 -0.0762 0.7625 0.0141
-6.750 -0.3082 0.01469 0.00904 -0.0753 0.7568 0.0145
-6.500 -0.2846 0.01408 0.00836 -0.0745 0.7498 0.0148
-6.250 -0.2607 0.01359 0.00777 -0.0738 0.7426 0.0151
-6.000 -0.2361 0.01319 0.00730 -0.0732 0.7356 0.0153
-5.750 -0.2116 0.01284 0.00687 -0.0725 0.7269 0.0156
-5.500 -0.1922 0.01170 0.00565 -0.0710 0.7194 0.0162
-5.250 -0.1697 0.01121 0.00510 -0.0700 0.7104 0.0166
-5.000 -0.1457 0.01087 0.00472 -0.0693 0.6989 0.0173
-4.750 -0.1218 0.01059 0.00437 -0.0685 0.6844 0.0180
-4.500 -0.0977 0.01039 0.00408 -0.0677 0.6677 0.0189
-4.250 -0.0737 0.01021 0.00381 -0.0669 0.6491 0.0195
-4.000 -0.0497 0.01008 0.00357 -0.0661 0.6275 0.0199
-3.500 -0.0045 0.00960 0.00286 -0.0639 0.5861 0.0224
-3.250 0.0198 0.00951 0.00267 -0.0632 0.5683 0.0237
-3.000 0.0446 0.00944 0.00252 -0.0626 0.5542 0.0250
-2.750 0.0692 0.00932 0.00235 -0.0619 0.5428 0.0286
-2.500 0.0937 0.00919 0.00222 -0.0612 0.5327 0.0391
-2.250 0.1168 0.00889 0.00208 -0.0604 0.5243 0.0881
-2.000 0.1402 0.00868 0.00200 -0.0596 0.5159 0.1364
-1.750 0.1635 0.00839 0.00192 -0.0589 0.5079 0.2059
-1.500 0.1845 0.00801 0.00184 -0.0577 0.4990 0.3093
-1.250 0.2056 0.00760 0.00176 -0.0566 0.4900 0.4244
-1.000 0.2241 0.00713 0.00170 -0.0548 0.4812 0.5642
-0.750 0.2443 0.00691 0.00174 -0.0533 0.4701 0.6642
-0.500 0.2685 0.00689 0.00175 -0.0525 0.4573 0.7027
-0.250 0.2925 0.00691 0.00177 -0.0517 0.4423 0.7291
0.000 0.3163 0.00696 0.00180 -0.0508 0.4253 0.7528
0.250 0.3395 0.00702 0.00184 -0.0498 0.4097 0.7808
0.500 0.3630 0.00706 0.00189 -0.0489 0.3976 0.8031
0.750 0.3875 0.00711 0.00194 -0.0482 0.3903 0.8218
1.000 0.4119 0.00716 0.00200 -0.0475 0.3845 0.8427
1.250 0.4359 0.00719 0.00208 -0.0466 0.3799 0.8686
1.500 0.4613 0.00721 0.00216 -0.0460 0.3767 0.8991
1.750 0.4897 0.00728 0.00226 -0.0461 0.3732 0.9250
2.000 0.5226 0.00740 0.00238 -0.0472 0.3704 0.9418
2.250 0.5560 0.00755 0.00249 -0.0485 0.3673 0.9541
2.500 0.5945 0.00769 0.00261 -0.0510 0.3651 0.9601
2.750 0.6273 0.00780 0.00271 -0.0521 0.3634 0.9686
3.000 0.6663 0.00793 0.00282 -0.0547 0.3612 0.9712
3.250 0.7027 0.00807 0.00294 -0.0568 0.3590 0.9746
3.500 0.7361 0.00823 0.00307 -0.0582 0.3566 0.9793
3.750 0.7697 0.00840 0.00320 -0.0596 0.3541 0.9831
4.000 0.8059 0.00858 0.00336 -0.0617 0.3515 0.9854
4.250 0.8417 0.00870 0.00348 -0.0636 0.3499 0.9880
4.500 0.8768 0.00881 0.00360 -0.0654 0.3486 0.9910
4.750 0.9109 0.00893 0.00372 -0.0670 0.3468 0.9938
5.000 0.9474 0.00903 0.00383 -0.0692 0.3449 0.9957
5.250 0.9832 0.00916 0.00396 -0.0712 0.3428 0.9978
5.500 1.0188 0.00931 0.00410 -0.0732 0.3404 0.9995
5.750 1.0419 0.00946 0.00425 -0.0725 0.3380 1.0000
6.000 1.0584 0.00965 0.00443 -0.0705 0.3354 1.0000
6.250 1.0785 0.00971 0.00452 -0.0691 0.3342 1.0000
6.500 1.0986 0.00978 0.00463 -0.0677 0.3324 1.0000
6.750 1.1186 0.00987 0.00475 -0.0663 0.3303 1.0000
7.000 1.1384 0.00998 0.00489 -0.0648 0.3279 1.0000
7.250 1.1572 0.01013 0.00504 -0.0632 0.3246 1.0000
7.500 1.1759 0.01027 0.00518 -0.0616 0.3186 1.0000
7.750 1.1980 0.01031 0.00523 -0.0607 0.3115 1.0000
8.000 1.2178 0.01043 0.00534 -0.0593 0.3028 1.0000
8.250 1.2374 0.01056 0.00546 -0.0579 0.2917 1.0000
8.750 1.2678 0.01103 0.00583 -0.0534 0.2690 1.0000
9.000 1.2802 0.01131 0.00610 -0.0507 0.2613 1.0000
9.250 1.2927 0.01165 0.00641 -0.0481 0.2546 1.0000
9.500 1.3068 0.01197 0.00673 -0.0458 0.2480 1.0000
9.750 1.3181 0.01244 0.00716 -0.0432 0.2389 1.0000
10.000 1.3334 0.01281 0.00753 -0.0414 0.2303 1.0000
10.250 1.3461 0.01331 0.00801 -0.0392 0.2222 1.0000
10.500 1.3640 0.01363 0.00835 -0.0379 0.2140 1.0000
10.750 1.3749 0.01428 0.00891 -0.0357 0.1906 1.0000
11.000 1.3649 0.01603 0.01033 -0.0309 0.1424 1.0000
11.250 1.3586 0.01775 0.01186 -0.0271 0.1095 1.0000
11.500 1.3612 0.01911 0.01313 -0.0246 0.0917 1.0000
11.750 1.3573 0.02096 0.01484 -0.0218 0.0677 1.0000
12.000 1.3634 0.02227 0.01612 -0.0201 0.0579 1.0000
12.250 1.3469 0.02526 0.01893 -0.0169 0.0289 1.0000
12.500 1.3582 0.02634 0.02006 -0.0160 0.0282 1.0000
12.750 1.3396 0.02981 0.02345 -0.0134 0.0099 1.0000
13.000 1.3382 0.03208 0.02575 -0.0121 0.0068 1.0000
13.250 1.3422 0.03398 0.02771 -0.0112 0.0061 1.0000
13.500 1.3451 0.03607 0.02987 -0.0105 0.0057 1.0000
13.750 1.3475 0.03829 0.03216 -0.0099 0.0055 1.0000
14.000 1.3494 0.04064 0.03458 -0.0095 0.0053 1.0000
14.250 1.3501 0.04322 0.03724 -0.0092 0.0052 1.0000
14.500 1.3471 0.04630 0.04042 -0.0090 0.0050 1.0000
14.750 1.3451 0.04935 0.04355 -0.0090 0.0048 1.0000
15.000 1.3447 0.05230 0.04658 -0.0091 0.0048 1.0000
15.250 1.3392 0.05590 0.05028 -0.0093 0.0047 1.0000
15.500 1.3333 0.05957 0.05405 -0.0096 0.0046 1.0000
15.750 1.3298 0.06301 0.05757 -0.0100 0.0046 1.0000
16.000 1.3252 0.06664 0.06129 -0.0104 0.0044 1.0000
16.250 1.3189 0.07051 0.06524 -0.0109 0.0045 1.0000
16.500 1.3120 0.07451 0.06934 -0.0116 0.0043 1.0000
16.750 1.3055 0.07855 0.07346 -0.0123 0.0045 1.0000
17.000 1.2991 0.08262 0.07762 -0.0131 0.0043 1.0000
17.250 1.2925 0.08674 0.08183 -0.0139 0.0042 1.0000
17.500 1.2854 0.09100 0.08617 -0.0149 0.0042 1.0000
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