DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: DEFIANT CANARD BL110 AIRFOIL (defcnd2-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.96 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-defcnd2-il-1000000-n5.txt Download as CSV file: xf-defcnd2-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.3732 0.16367 0.16193 -0.0242 1.0000 0.0053
-15.250 -0.3679 0.16005 0.15831 -0.0256 1.0000 0.0054
-13.750 -0.8019 0.03954 0.03694 -0.0880 0.9758 0.0071
-13.500 -0.7762 0.03422 0.03134 -0.0992 0.9537 0.0071
-13.250 -0.7336 0.03135 0.02824 -0.1084 0.9322 0.0073
-13.000 -0.7076 0.02982 0.02644 -0.1119 0.8880 0.0073
-12.750 -0.7273 0.02744 0.02371 -0.1079 0.8539 0.0073
-12.500 -0.7251 0.02654 0.02266 -0.1051 0.8363 0.0074
-12.250 -0.7252 0.02546 0.02141 -0.1018 0.8243 0.0075
-12.000 -0.7244 0.02444 0.02024 -0.0982 0.8143 0.0075
-11.750 -0.7199 0.02364 0.01931 -0.0949 0.8060 0.0076
-11.500 -0.7115 0.02281 0.01835 -0.0923 0.7994 0.0077
-11.250 -0.7008 0.02188 0.01727 -0.0900 0.7927 0.0077
-11.000 -0.6868 0.02113 0.01640 -0.0882 0.7871 0.0079
-10.750 -0.6714 0.02037 0.01551 -0.0865 0.7818 0.0080
-10.500 -0.6550 0.01964 0.01466 -0.0849 0.7763 0.0081
-10.250 -0.6382 0.01889 0.01378 -0.0834 0.7716 0.0083
-10.000 -0.6197 0.01821 0.01299 -0.0821 0.7671 0.0084
-9.750 -0.5997 0.01765 0.01233 -0.0809 0.7616 0.0086
-9.500 -0.5798 0.01710 0.01166 -0.0797 0.7552 0.0087
-9.250 -0.5585 0.01658 0.01104 -0.0788 0.7492 0.0088
-9.000 -0.5364 0.01616 0.01054 -0.0779 0.7434 0.0089
-8.750 -0.5171 0.01540 0.00967 -0.0766 0.7386 0.0092
-8.500 -0.4958 0.01481 0.00901 -0.0756 0.7333 0.0094
-8.250 -0.4729 0.01442 0.00857 -0.0748 0.7273 0.0096
-8.000 -0.4498 0.01401 0.00810 -0.0741 0.7213 0.0097
-7.750 -0.4261 0.01367 0.00770 -0.0734 0.7138 0.0099
-7.500 -0.4025 0.01332 0.00728 -0.0726 0.7060 0.0101
-7.250 -0.3789 0.01300 0.00689 -0.0719 0.6962 0.0104
-7.000 -0.3554 0.01268 0.00649 -0.0711 0.6821 0.0106
-6.750 -0.3321 0.01241 0.00612 -0.0703 0.6650 0.0109
-6.500 -0.3099 0.01221 0.00575 -0.0692 0.6343 0.0111
-6.250 -0.2875 0.01204 0.00543 -0.0682 0.6028 0.0114
-6.000 -0.2648 0.01191 0.00515 -0.0672 0.5725 0.0116
-5.750 -0.2414 0.01181 0.00491 -0.0664 0.5480 0.0118
-5.500 -0.2180 0.01151 0.00453 -0.0656 0.5368 0.0123
-5.250 -0.1940 0.01126 0.00422 -0.0649 0.5282 0.0127
-5.000 -0.1688 0.01110 0.00402 -0.0644 0.5203 0.0133
-4.750 -0.1438 0.01094 0.00381 -0.0639 0.5120 0.0138
-4.500 -0.1186 0.01079 0.00361 -0.0633 0.5035 0.0143
-4.250 -0.0932 0.01064 0.00341 -0.0629 0.4962 0.0148
-4.000 -0.0676 0.01051 0.00322 -0.0624 0.4885 0.0152
-3.750 -0.0420 0.01039 0.00306 -0.0620 0.4804 0.0156
-3.500 -0.0170 0.01022 0.00283 -0.0614 0.4713 0.0166
-3.250 0.0085 0.01011 0.00268 -0.0609 0.4617 0.0176
-3.000 0.0340 0.01003 0.00255 -0.0605 0.4499 0.0187
-2.750 0.0593 0.01000 0.00244 -0.0600 0.4337 0.0197
-2.500 0.0836 0.01000 0.00233 -0.0593 0.4101 0.0218
-2.250 0.1078 0.01000 0.00226 -0.0586 0.3890 0.0262
-2.000 0.1318 0.00991 0.00219 -0.0580 0.3775 0.0459
-1.750 0.1564 0.00981 0.00212 -0.0574 0.3698 0.0683
-1.250 0.2059 0.00956 0.00203 -0.0563 0.3605 0.1315
-1.000 0.2308 0.00943 0.00199 -0.0558 0.3577 0.1699
-0.750 0.2546 0.00922 0.00196 -0.0551 0.3550 0.2325
-0.250 0.2995 0.00864 0.00190 -0.0533 0.3507 0.4153
0.000 0.3195 0.00820 0.00187 -0.0519 0.3494 0.5487
0.250 0.3396 0.00790 0.00192 -0.0504 0.3482 0.6656
0.500 0.3644 0.00786 0.00195 -0.0498 0.3468 0.6987
0.750 0.3902 0.00787 0.00199 -0.0494 0.3454 0.7181
1.000 0.4154 0.00786 0.00203 -0.0488 0.3441 0.7381
1.250 0.4400 0.00785 0.00208 -0.0481 0.3427 0.7647
1.500 0.4636 0.00782 0.00214 -0.0472 0.3413 0.7966
1.750 0.4873 0.00781 0.00221 -0.0464 0.3393 0.8247
2.000 0.5119 0.00784 0.00228 -0.0457 0.3377 0.8458
2.250 0.5370 0.00788 0.00235 -0.0451 0.3361 0.8635
2.500 0.5628 0.00791 0.00243 -0.0447 0.3350 0.8806
2.750 0.5898 0.00794 0.00250 -0.0446 0.3343 0.8983
3.000 0.6187 0.00798 0.00259 -0.0449 0.3333 0.9154
3.250 0.6506 0.00806 0.00269 -0.0459 0.3322 0.9307
3.500 0.6854 0.00816 0.00280 -0.0475 0.3306 0.9429
3.750 0.7205 0.00827 0.00291 -0.0493 0.3284 0.9531
4.000 0.7581 0.00841 0.00304 -0.0517 0.3262 0.9589
4.250 0.7933 0.00854 0.00316 -0.0535 0.3241 0.9655
4.500 0.8282 0.00869 0.00329 -0.0553 0.3222 0.9701
4.750 0.8628 0.00884 0.00344 -0.0570 0.3203 0.9738
5.000 0.8946 0.00894 0.00355 -0.0581 0.3191 0.9787
5.250 0.9252 0.00904 0.00367 -0.0589 0.3176 0.9831
5.500 0.9583 0.00915 0.00379 -0.0603 0.3156 0.9862
5.750 0.9900 0.00927 0.00392 -0.0614 0.3131 0.9898
6.000 1.0203 0.00940 0.00406 -0.0622 0.3103 0.9931
6.250 1.0515 0.00955 0.00421 -0.0632 0.3073 0.9961
6.500 1.0837 0.00968 0.00436 -0.0645 0.3045 0.9983
6.750 1.1162 0.00980 0.00450 -0.0658 0.3006 0.9997
7.000 1.1389 0.00992 0.00463 -0.0650 0.2952 1.0000
7.250 1.1576 0.01007 0.00476 -0.0634 0.2857 1.0000
7.500 1.1703 0.01045 0.00498 -0.0607 0.2626 1.0000
7.750 1.1831 0.01082 0.00527 -0.0581 0.2502 1.0000
8.000 1.1959 0.01119 0.00559 -0.0555 0.2400 1.0000
8.250 1.2099 0.01143 0.00583 -0.0530 0.2348 1.0000
8.500 1.2244 0.01163 0.00605 -0.0506 0.2312 1.0000
8.750 1.2380 0.01191 0.00632 -0.0481 0.2266 1.0000
9.000 1.2527 0.01220 0.00661 -0.0459 0.2223 1.0000
9.250 1.2710 0.01240 0.00686 -0.0444 0.2193 1.0000
9.500 1.2867 0.01272 0.00718 -0.0426 0.2116 1.0000
9.750 1.2987 0.01323 0.00760 -0.0403 0.1911 1.0000
10.000 1.2826 0.01506 0.00902 -0.0340 0.1295 1.0000
10.250 1.2823 0.01631 0.01012 -0.0304 0.1012 1.0000
10.500 1.2864 0.01745 0.01116 -0.0277 0.0816 1.0000
10.750 1.2897 0.01872 0.01233 -0.0252 0.0622 1.0000
11.000 1.2973 0.01981 0.01338 -0.0233 0.0513 1.0000
11.250 1.2981 0.02140 0.01489 -0.0210 0.0346 1.0000
11.500 1.3002 0.02300 0.01644 -0.0190 0.0232 1.0000
11.750 1.3012 0.02477 0.01819 -0.0171 0.0134 1.0000
12.000 1.3077 0.02621 0.01965 -0.0158 0.0093 1.0000
12.250 1.3064 0.02831 0.02177 -0.0142 0.0042 1.0000
12.500 1.3167 0.02956 0.02307 -0.0134 0.0044 1.0000
12.750 1.3211 0.03132 0.02489 -0.0124 0.0037 1.0000
13.000 1.3257 0.03315 0.02678 -0.0116 0.0034 1.0000
13.250 1.3312 0.03496 0.02865 -0.0109 0.0032 1.0000
13.500 1.3355 0.03695 0.03070 -0.0103 0.0031 1.0000
13.750 1.3394 0.03905 0.03288 -0.0098 0.0030 1.0000
14.000 1.3423 0.04134 0.03523 -0.0095 0.0030 1.0000
14.250 1.3448 0.04374 0.03771 -0.0092 0.0030 1.0000
14.500 1.3450 0.04647 0.04052 -0.0091 0.0029 1.0000
14.750 1.3463 0.04914 0.04327 -0.0091 0.0029 1.0000
15.000 1.3457 0.05211 0.04631 -0.0092 0.0029 1.0000
15.250 1.3437 0.05529 0.04957 -0.0094 0.0028 1.0000
15.500 1.3392 0.05877 0.05315 -0.0097 0.0027 1.0000
15.750 1.3375 0.06196 0.05641 -0.0100 0.0027 1.0000
16.000 1.3330 0.06555 0.06008 -0.0104 0.0026 1.0000
16.250 1.3286 0.06916 0.06377 -0.0109 0.0027 1.0000
16.500 1.3224 0.07303 0.06772 -0.0115 0.0025 1.0000
16.750 1.3180 0.07675 0.07153 -0.0121 0.0026 1.0000
17.000 1.3125 0.08066 0.07552 -0.0128 0.0025 1.0000
17.250 1.3065 0.08464 0.07957 -0.0136 0.0024 1.0000
17.500 1.3004 0.08870 0.08371 -0.0145 0.0024 1.0000
17.750 1.2929 0.09302 0.08813 -0.0155 0.0023 1.0000
18.000 1.2898 0.09673 0.09191 -0.0164 0.0023 1.0000
18.250 1.2829 0.10097 0.09623 -0.0175 0.0023 1.0000
18.500 1.2758 0.10531 0.10064 -0.0186 0.0023 1.0000
18.750 1.2700 0.10946 0.10487 -0.0198 0.0023 1.0000
19.000 1.2655 0.11346 0.10894 -0.0210 0.0022 1.0000
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Polar data table (+)
Polar graphs
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