DEFIANT CANARD BL20 AIRFOIL (defcnd1-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: DEFIANT CANARD BL20 AIRFOIL (defcnd1-il) Reynolds number: 200,000 Max Cl/Cd: 52.84 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-defcnd1-il-200000.txt Download as CSV file: xf-defcnd1-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: DEFIANT CANARD BL20 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.2905 0.18046 0.17682 -0.0265 1.0000 0.0622
-17.000 -0.3044 0.17582 0.17223 -0.0317 1.0000 0.0649
-16.750 -0.6970 0.08241 0.07762 -0.0764 1.0000 0.0435
-16.250 -0.6827 0.07819 0.07355 -0.0775 1.0000 0.0451
-16.000 -0.7039 0.07189 0.06710 -0.0814 1.0000 0.0455
-15.750 -0.7204 0.06657 0.06165 -0.0846 1.0000 0.0459
-15.500 -0.7352 0.06170 0.05666 -0.0875 1.0000 0.0465
-15.250 -0.7481 0.05723 0.05206 -0.0900 1.0000 0.0471
-15.000 -0.7612 0.05289 0.04755 -0.0925 1.0000 0.0478
-14.750 -0.7362 0.04950 0.04415 -0.0985 0.9264 0.0494
-14.500 -0.6852 0.04480 0.03903 -0.1124 0.8529 0.0524
-14.250 -0.6716 0.04182 0.03573 -0.1166 0.8169 0.0543
-14.000 -0.6621 0.03997 0.03377 -0.1180 0.7967 0.0561
-13.750 -0.6640 0.03768 0.03123 -0.1185 0.7834 0.0580
-13.500 -0.6640 0.03576 0.02916 -0.1183 0.7722 0.0598
-13.250 -0.6598 0.03435 0.02769 -0.1179 0.7630 0.0618
-13.000 -0.6617 0.03266 0.02583 -0.1169 0.7543 0.0643
-12.750 -0.6596 0.03143 0.02453 -0.1157 0.7467 0.0666
-12.500 -0.6577 0.03034 0.02339 -0.1141 0.7395 0.0694
-12.250 -0.6564 0.02925 0.02219 -0.1121 0.7327 0.0725
-12.000 -0.6519 0.02861 0.02149 -0.1100 0.7269 0.0756
-11.750 -0.6496 0.02782 0.02059 -0.1073 0.7212 0.0794
-11.500 -0.6437 0.02742 0.02021 -0.1046 0.7151 0.0828
-11.250 -0.6412 0.02694 0.01954 -0.1013 0.7097 0.0868
-11.000 -0.6325 0.02690 0.01949 -0.0986 0.7047 0.0902
-10.750 -0.6252 0.02650 0.01892 -0.0958 0.6995 0.0948
-10.500 -0.6094 0.02640 0.01889 -0.0941 0.6943 0.0985
-10.250 -0.5991 0.02617 0.01839 -0.0915 0.6898 0.1032
-10.000 -0.5792 0.02599 0.01827 -0.0904 0.6856 0.1071
-9.750 -0.5639 0.02581 0.01798 -0.0886 0.6809 0.1117
-9.500 -0.5455 0.02539 0.01753 -0.0873 0.6759 0.1159
-9.250 -0.5255 0.02523 0.01735 -0.0861 0.6712 0.1203
-9.000 -0.5093 0.02508 0.01692 -0.0842 0.6674 0.1249
-8.750 -0.4851 0.02465 0.01658 -0.0839 0.6638 0.1294
-8.500 -0.4654 0.02446 0.01635 -0.0826 0.6594 0.1343
-8.250 -0.4447 0.02399 0.01581 -0.0816 0.6548 0.1391
-8.000 -0.4213 0.02372 0.01557 -0.0809 0.6505 0.1440
-7.750 -0.3998 0.02353 0.01520 -0.0798 0.6469 0.1489
-7.500 -0.3758 0.02301 0.01462 -0.0793 0.6436 0.1534
-7.250 -0.3522 0.02267 0.01436 -0.0786 0.6395 0.1578
-7.000 -0.3293 0.02242 0.01402 -0.0777 0.6353 0.1623
-6.750 -0.3053 0.02193 0.01346 -0.0771 0.6313 0.1664
-6.500 -0.2799 0.02150 0.01304 -0.0767 0.6278 0.1709
-6.250 -0.2547 0.02126 0.01270 -0.0761 0.6246 0.1755
-6.000 -0.2308 0.02114 0.01246 -0.0754 0.6211 0.1796
-5.750 -0.2063 0.02061 0.01206 -0.0749 0.6171 0.1842
-5.500 -0.1819 0.02035 0.01182 -0.0743 0.6132 0.1891
-5.250 -0.1567 0.02012 0.01151 -0.0737 0.6096 0.1942
-5.000 -0.1311 0.01972 0.01109 -0.0732 0.6064 0.1995
-4.750 -0.1056 0.01951 0.01085 -0.0728 0.6035 0.2056
-4.500 -0.0817 0.01940 0.01074 -0.0720 0.5999 0.2120
-4.250 -0.0590 0.01911 0.01059 -0.0712 0.5961 0.2194
-4.000 -0.0347 0.01894 0.01042 -0.0705 0.5923 0.2289
-3.750 -0.0111 0.01861 0.01018 -0.0697 0.5890 0.2408
-3.500 0.0133 0.01832 0.00993 -0.0689 0.5861 0.2582
-3.250 0.0373 0.01810 0.00980 -0.0682 0.5834 0.2877
-3.000 0.0574 0.01799 0.00994 -0.0669 0.5800 0.3280
-2.750 0.0787 0.01801 0.01011 -0.0657 0.5761 0.3672
-2.500 0.1020 0.01804 0.01022 -0.0647 0.5725 0.3965
-2.250 0.1272 0.01806 0.01023 -0.0640 0.5692 0.4203
-2.000 0.1536 0.01807 0.01019 -0.0635 0.5664 0.4399
-1.750 0.1808 0.01815 0.01021 -0.0632 0.5639 0.4568
-1.500 0.2036 0.01836 0.01045 -0.0622 0.5605 0.4717
-1.250 0.2264 0.01849 0.01064 -0.0613 0.5564 0.4856
-1.000 0.2512 0.01851 0.01069 -0.0606 0.5527 0.4992
-0.750 0.2776 0.01850 0.01062 -0.0602 0.5496 0.5136
-0.500 0.3051 0.01842 0.01055 -0.0599 0.5470 0.5270
-0.250 0.3335 0.01844 0.01052 -0.0599 0.5447 0.5404
0.000 0.3551 0.01864 0.01079 -0.0588 0.5410 0.5539
0.250 0.3770 0.01871 0.01099 -0.0578 0.5368 0.5674
0.500 0.4016 0.01870 0.01103 -0.0572 0.5332 0.5836
0.750 0.4273 0.01863 0.01101 -0.0566 0.5304 0.6038
1.000 0.4544 0.01853 0.01095 -0.0562 0.5279 0.6268
1.250 0.4827 0.01848 0.01094 -0.0561 0.5255 0.6522
1.500 0.4998 0.01865 0.01135 -0.0543 0.5215 0.6814
1.750 0.5193 0.01869 0.01164 -0.0527 0.5174 0.7210
2.000 0.5443 0.01860 0.01180 -0.0518 0.5141 0.7821
2.250 0.5914 0.01853 0.01191 -0.0549 0.5111 0.8658
2.500 0.6605 0.01858 0.01187 -0.0624 0.5081 0.9178
2.750 0.7115 0.01899 0.01227 -0.0670 0.5043 0.9480
3.000 0.7601 0.01944 0.01275 -0.0713 0.4995 0.9674
3.250 0.8139 0.01959 0.01284 -0.0765 0.4955 0.9820
3.500 0.8707 0.01953 0.01266 -0.0821 0.4922 0.9929
3.750 0.9258 0.01946 0.01243 -0.0875 0.4894 1.0000
4.000 0.9368 0.01985 0.01285 -0.0850 0.4861 1.0000
4.250 0.9449 0.02025 0.01332 -0.0820 0.4819 1.0000
4.500 0.9604 0.02043 0.01348 -0.0800 0.4783 1.0000
4.750 0.9811 0.02048 0.01347 -0.0788 0.4753 1.0000
5.000 1.0065 0.02048 0.01337 -0.0783 0.4728 1.0000
5.250 1.0320 0.02067 0.01344 -0.0779 0.4702 1.0000
5.500 1.0339 0.02128 0.01420 -0.0738 0.4658 1.0000
5.750 1.0466 0.02161 0.01457 -0.0714 0.4618 1.0000
6.000 1.0671 0.02171 0.01462 -0.0702 0.4585 1.0000
6.250 1.0940 0.02170 0.01453 -0.0699 0.4558 1.0000
6.500 1.1256 0.02175 0.01445 -0.0705 0.4532 1.0000
6.750 1.1255 0.02245 0.01531 -0.0662 0.4489 1.0000
7.000 1.1342 0.02289 0.01580 -0.0632 0.4447 1.0000
7.250 1.1539 0.02304 0.01594 -0.0619 0.4413 1.0000
7.500 1.1823 0.02303 0.01585 -0.0620 0.4385 1.0000
7.750 1.2175 0.02304 0.01572 -0.0631 0.4359 1.0000
8.000 1.2102 0.02390 0.01676 -0.0579 0.4315 1.0000
8.250 1.2138 0.02445 0.01738 -0.0542 0.4272 1.0000
8.500 1.2333 0.02460 0.01752 -0.0530 0.4238 1.0000
8.750 1.2651 0.02454 0.01737 -0.0535 0.4210 1.0000
9.000 1.3002 0.02462 0.01736 -0.0548 0.4181 1.0000
9.250 1.2726 0.02579 0.01873 -0.0466 0.4135 1.0000
9.500 1.2668 0.02648 0.01948 -0.0418 0.4094 1.0000
9.750 1.2897 0.02656 0.01954 -0.0411 0.4061 1.0000
10.000 1.3302 0.02638 0.01926 -0.0430 0.4034 1.0000
10.250 1.3401 0.02699 0.01990 -0.0407 0.3999 1.0000
10.500 1.3004 0.02904 0.02215 -0.0329 0.3950 1.0000
10.750 1.3072 0.02979 0.02292 -0.0309 0.3909 1.0000
11.000 1.3432 0.02943 0.02249 -0.0316 0.3880 1.0000
11.250 1.3945 0.02880 0.02174 -0.0342 0.3853 1.0000
11.500 1.3222 0.03310 0.02635 -0.0257 0.3792 1.0000
11.750 1.3147 0.03504 0.02836 -0.0236 0.3744 1.0000
12.000 1.3544 0.03420 0.02745 -0.0242 0.3718 1.0000
12.250 1.4062 0.03292 0.02607 -0.0257 0.3695 1.0000
12.500 1.2719 0.04381 0.03735 -0.0186 0.3587 1.0000
12.750 1.3098 0.04272 0.03623 -0.0187 0.3566 1.0000
13.000 1.3603 0.04078 0.03422 -0.0192 0.3550 1.0000
13.250 1.4174 0.03862 0.03197 -0.0203 0.3532 1.0000
13.500 1.2552 0.05400 0.04772 -0.0155 0.3394 1.0000
13.750 1.3083 0.05128 0.04496 -0.0156 0.3388 1.0000
14.000 1.3652 0.04842 0.04204 -0.0159 0.3379 1.0000
14.250 1.4267 0.04549 0.03903 -0.0166 0.3367 1.0000
14.500 1.2571 0.06345 0.05732 -0.0138 0.3217 1.0000
14.750 1.3120 0.06016 0.05401 -0.0137 0.3215 1.0000
15.000 1.3694 0.05689 0.05069 -0.0137 0.3210 1.0000
15.250 1.4322 0.05341 0.04715 -0.0139 0.3201 1.0000
15.500 1.2576 0.07383 0.06786 -0.0131 0.3043 1.0000
15.750 1.3120 0.07023 0.06425 -0.0127 0.3043 1.0000
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Polar data table (+)
Polar graphs
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