DEFIANT CANARD BL20 AIRFOIL (defcnd1-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: DEFIANT CANARD BL20 AIRFOIL (defcnd1-il) Reynolds number: 500,000 Max Cl/Cd: 93.72 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-defcnd1-il-500000.txt Download as CSV file: xf-defcnd1-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.7602 0.09119 0.08727 -0.0613 1.0000 0.0255
-17.500 -0.7665 0.08680 0.08283 -0.0636 1.0000 0.0258
-17.250 -0.7735 0.08232 0.07830 -0.0660 1.0000 0.0261
-17.000 -0.7802 0.07796 0.07389 -0.0683 1.0000 0.0263
-16.750 -0.7818 0.07268 0.06852 -0.0724 0.9485 0.0267
-16.500 -0.7080 0.06251 0.05796 -0.0991 0.8763 0.0280
-16.250 -0.7005 0.05758 0.05249 -0.1061 0.7768 0.0287
-16.000 -0.7106 0.05381 0.04850 -0.1078 0.7546 0.0292
-15.750 -0.7199 0.05020 0.04474 -0.1093 0.7417 0.0296
-15.500 -0.7277 0.04680 0.04120 -0.1107 0.7318 0.0302
-15.250 -0.7360 0.04348 0.03775 -0.1119 0.7237 0.0304
-15.000 -0.7392 0.04065 0.03479 -0.1128 0.7165 0.0311
-14.750 -0.7505 0.03720 0.03125 -0.1138 0.7099 0.0316
-14.500 -0.7576 0.03420 0.02815 -0.1145 0.7037 0.0322
-14.250 -0.7615 0.03159 0.02547 -0.1150 0.6979 0.0329
-14.000 -0.7627 0.02945 0.02322 -0.1149 0.6920 0.0337
-13.750 -0.7619 0.02772 0.02134 -0.1143 0.6861 0.0348
-13.500 -0.7668 0.02581 0.01938 -0.1132 0.6814 0.0357
-13.250 -0.7682 0.02434 0.01787 -0.1115 0.6766 0.0367
-13.000 -0.7651 0.02327 0.01671 -0.1095 0.6717 0.0383
-12.750 -0.7637 0.02225 0.01560 -0.1070 0.6670 0.0398
-12.500 -0.7606 0.02135 0.01466 -0.1044 0.6625 0.0415
-12.250 -0.7539 0.02060 0.01387 -0.1018 0.6583 0.0439
-12.000 -0.7488 0.01984 0.01309 -0.0989 0.6538 0.0466
-11.750 -0.7418 0.01920 0.01240 -0.0959 0.6495 0.0498
-11.500 -0.7327 0.01874 0.01187 -0.0931 0.6453 0.0538
-11.250 -0.7234 0.01826 0.01139 -0.0903 0.6417 0.0579
-11.000 -0.7094 0.01778 0.01092 -0.0882 0.6381 0.0627
-10.750 -0.6927 0.01736 0.01050 -0.0864 0.6341 0.0678
-10.500 -0.6739 0.01702 0.01014 -0.0850 0.6301 0.0731
-10.250 -0.6529 0.01679 0.00984 -0.0838 0.6259 0.0785
-10.000 -0.6316 0.01656 0.00961 -0.0827 0.6220 0.0833
-9.750 -0.6089 0.01634 0.00938 -0.0818 0.6188 0.0879
-9.500 -0.5850 0.01619 0.00921 -0.0811 0.6151 0.0925
-9.250 -0.5619 0.01599 0.00897 -0.0802 0.6115 0.0963
-9.000 -0.5377 0.01587 0.00881 -0.0795 0.6078 0.1002
-8.750 -0.5122 0.01584 0.00866 -0.0789 0.6038 0.1036
-8.500 -0.4898 0.01557 0.00843 -0.0780 0.6006 0.1071
-8.250 -0.4646 0.01546 0.00829 -0.0774 0.5973 0.1105
-8.000 -0.4384 0.01540 0.00814 -0.0769 0.5939 0.1135
-7.750 -0.4161 0.01506 0.00782 -0.0759 0.5906 0.1168
-7.500 -0.3912 0.01492 0.00765 -0.0753 0.5873 0.1199
-7.250 -0.3652 0.01491 0.00753 -0.0749 0.5834 0.1233
-7.000 -0.3409 0.01467 0.00729 -0.0742 0.5805 0.1270
-6.750 -0.3162 0.01446 0.00711 -0.0736 0.5774 0.1308
-6.500 -0.2903 0.01433 0.00695 -0.0731 0.5742 0.1342
-6.250 -0.2640 0.01424 0.00678 -0.0726 0.5711 0.1366
-6.000 -0.2405 0.01389 0.00643 -0.0718 0.5680 0.1400
-5.750 -0.2156 0.01373 0.00623 -0.0712 0.5645 0.1432
-5.500 -0.1898 0.01359 0.00607 -0.0707 0.5615 0.1462
-5.250 -0.1635 0.01345 0.00591 -0.0703 0.5586 0.1490
-5.000 -0.1382 0.01324 0.00568 -0.0697 0.5556 0.1521
-4.750 -0.1134 0.01300 0.00546 -0.0691 0.5526 0.1562
-4.500 -0.0874 0.01285 0.00528 -0.0686 0.5495 0.1600
-4.250 -0.0609 0.01277 0.00513 -0.0682 0.5463 0.1637
-4.000 -0.0355 0.01262 0.00498 -0.0677 0.5431 0.1688
-3.750 -0.0098 0.01244 0.00484 -0.0672 0.5405 0.1747
-3.500 0.0166 0.01230 0.00471 -0.0667 0.5377 0.1810
-3.250 0.0420 0.01209 0.00456 -0.0662 0.5347 0.1918
-3.000 0.0674 0.01188 0.00440 -0.0657 0.5316 0.2079
-2.750 0.0920 0.01162 0.00426 -0.0650 0.5287 0.2396
-2.500 0.1165 0.01145 0.00421 -0.0645 0.5253 0.2872
-2.250 0.1416 0.01125 0.00419 -0.0639 0.5230 0.3273
-2.000 0.1676 0.01114 0.00418 -0.0634 0.5202 0.3556
-1.750 0.1942 0.01108 0.00417 -0.0631 0.5170 0.3769
-1.500 0.2211 0.01103 0.00415 -0.0627 0.5140 0.3939
-1.250 0.2483 0.01103 0.00413 -0.0625 0.5111 0.4087
-1.000 0.2756 0.01108 0.00415 -0.0623 0.5081 0.4231
-0.750 0.3025 0.01110 0.00420 -0.0620 0.5053 0.4353
-0.500 0.3297 0.01110 0.00421 -0.0617 0.5025 0.4467
-0.250 0.3563 0.01107 0.00422 -0.0614 0.4994 0.4574
0.000 0.3837 0.01108 0.00423 -0.0611 0.4964 0.4680
0.250 0.4104 0.01107 0.00423 -0.0608 0.4936 0.4784
0.500 0.4377 0.01113 0.00424 -0.0606 0.4905 0.4892
0.750 0.4644 0.01118 0.00431 -0.0604 0.4874 0.4998
1.000 0.4909 0.01117 0.00434 -0.0600 0.4847 0.5109
1.250 0.5168 0.01114 0.00438 -0.0596 0.4818 0.5242
1.500 0.5430 0.01113 0.00440 -0.0592 0.4787 0.5386
1.750 0.5689 0.01111 0.00441 -0.0587 0.4757 0.5542
2.000 0.5946 0.01111 0.00444 -0.0583 0.4725 0.5718
2.250 0.6199 0.01114 0.00454 -0.0578 0.4696 0.5941
2.500 0.6433 0.01105 0.00461 -0.0569 0.4669 0.6268
2.750 0.6649 0.01090 0.00468 -0.0556 0.4637 0.6799
3.000 0.6840 0.01067 0.00478 -0.0536 0.4607 0.7682
3.250 0.7111 0.01054 0.00493 -0.0532 0.4577 0.8676
3.500 0.7660 0.01074 0.00516 -0.0586 0.4539 0.9255
3.750 0.8167 0.01093 0.00537 -0.0633 0.4504 0.9483
4.000 0.8577 0.01108 0.00553 -0.0660 0.4469 0.9633
4.250 0.9014 0.01125 0.00569 -0.0692 0.4434 0.9721
4.500 0.9406 0.01142 0.00581 -0.0716 0.4399 0.9805
4.750 0.9833 0.01166 0.00595 -0.0748 0.4358 0.9861
5.000 1.0240 0.01181 0.00613 -0.0776 0.4326 0.9923
5.250 1.0678 0.01191 0.00625 -0.0810 0.4289 0.9969
5.500 1.1073 0.01202 0.00634 -0.0837 0.4251 1.0000
5.750 1.1249 0.01216 0.00643 -0.0819 0.4218 1.0000
6.000 1.1432 0.01238 0.00659 -0.0803 0.4183 1.0000
6.250 1.1600 0.01248 0.00675 -0.0783 0.4155 1.0000
6.500 1.1771 0.01261 0.00690 -0.0764 0.4122 1.0000
6.750 1.1941 0.01275 0.00705 -0.0745 0.4088 1.0000
7.000 1.2109 0.01292 0.00718 -0.0726 0.4054 1.0000
7.250 1.2285 0.01318 0.00737 -0.0708 0.4016 1.0000
7.500 1.2440 0.01333 0.00758 -0.0687 0.3987 1.0000
7.750 1.2596 0.01350 0.00779 -0.0666 0.3953 1.0000
8.000 1.2745 0.01369 0.00798 -0.0643 0.3917 1.0000
8.250 1.2888 0.01392 0.00819 -0.0620 0.3882 1.0000
8.500 1.3023 0.01422 0.00843 -0.0596 0.3846 1.0000
8.750 1.3113 0.01441 0.00869 -0.0563 0.3817 1.0000
9.000 1.3221 0.01465 0.00897 -0.0535 0.3783 1.0000
9.250 1.3338 0.01493 0.00926 -0.0509 0.3746 1.0000
9.500 1.3459 0.01528 0.00958 -0.0486 0.3709 1.0000
9.750 1.3594 0.01568 0.00998 -0.0466 0.3673 1.0000
10.000 1.3714 0.01608 0.01045 -0.0445 0.3639 1.0000
10.250 1.3837 0.01653 0.01094 -0.0425 0.3602 1.0000
10.500 1.3955 0.01706 0.01146 -0.0407 0.3564 1.0000
10.750 1.4084 0.01767 0.01201 -0.0391 0.3522 1.0000
11.000 1.4193 0.01834 0.01278 -0.0375 0.3489 1.0000
11.250 1.4306 0.01907 0.01357 -0.0361 0.3452 1.0000
11.500 1.4413 0.01990 0.01441 -0.0348 0.3413 1.0000
11.750 1.4523 0.02079 0.01526 -0.0335 0.3373 1.0000
12.000 1.4626 0.02179 0.01633 -0.0325 0.3336 1.0000
12.250 1.4721 0.02291 0.01752 -0.0316 0.3297 1.0000
12.500 1.4814 0.02408 0.01871 -0.0307 0.3258 1.0000
12.750 1.4908 0.02522 0.01982 -0.0297 0.3217 1.0000
13.000 1.4994 0.02648 0.02113 -0.0289 0.3179 1.0000
13.250 1.5061 0.02795 0.02268 -0.0282 0.3140 1.0000
13.500 1.5126 0.02942 0.02417 -0.0274 0.3099 1.0000
13.750 1.5201 0.03072 0.02542 -0.0265 0.3053 1.0000
14.000 1.5249 0.03238 0.02716 -0.0258 0.3016 1.0000
14.250 1.5280 0.03421 0.02907 -0.0251 0.2973 1.0000
14.500 1.5317 0.03597 0.03082 -0.0244 0.2926 1.0000
14.750 1.5381 0.03746 0.03228 -0.0237 0.2882 1.0000
15.000 1.5389 0.03966 0.03460 -0.0232 0.2841 1.0000
15.250 1.5420 0.04164 0.03663 -0.0228 0.2802 1.0000
15.500 1.5468 0.04340 0.03836 -0.0223 0.2759 1.0000
15.750 1.5501 0.04538 0.04038 -0.0218 0.2717 1.0000
16.000 1.5511 0.04772 0.04280 -0.0216 0.2676 1.0000
16.250 1.5532 0.04992 0.04503 -0.0213 0.2635 1.0000
16.500 1.5591 0.05161 0.04667 -0.0209 0.2591 1.0000
16.750 1.5576 0.05430 0.04947 -0.0207 0.2551 1.0000
17.000 1.5579 0.05680 0.05203 -0.0206 0.2510 1.0000
17.250 1.5588 0.05918 0.05440 -0.0205 0.2464 1.0000
17.500 1.5612 0.06140 0.05664 -0.0203 0.2423 1.0000
17.750 1.5576 0.06443 0.05978 -0.0204 0.2379 1.0000
18.000 1.5563 0.06716 0.06252 -0.0204 0.2333 1.0000
18.250 1.5603 0.06921 0.06454 -0.0203 0.2290 1.0000
18.500 1.5553 0.07252 0.06796 -0.0205 0.2252 1.0000
18.750 1.5541 0.07532 0.07081 -0.0207 0.2209 1.0000
19.000 1.5538 0.07796 0.07345 -0.0208 0.2169 1.0000
19.250 1.5533 0.08069 0.07623 -0.0210 0.2131 1.0000
|
Polar data table (+)
Polar graphs
<< Back to DEFIANT CANARD BL20 AIRFOIL (defcnd1-il)