DEFIANT CANARD BL145 AIRFOIL (defcnd3-il)
DEFIANT CANARD BL145 AIRFOIL - Rutan DEFIANT canard BL145 airfoil
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(defcnd3-il) DEFIANT CANARD BL145 AIRFOIL Rutan DEFIANT canard BL145 airfoil Max thickness 11.5% at 28.6% chord. Max camber 2.4% at 28.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
DEFIANT CANARD BL145 AIRFOIL
40.0 40.0
0.0000000 0.0000000
0.0016214 0.0121587
0.0064749 0.0203965
0.0145291 0.0294052
0.0257318 0.0375583
0.0400103 0.0451446
0.0572720 0.0521572
0.0774050 0.0587942
0.1002786 0.0650665
0.1257446 0.0705051
0.1536378 0.0747044
0.1837773 0.0775320
0.2159677 0.0792998
0.2500001 0.0806789
0.2856538 0.0812013
0.3226977 0.0806903
0.3608914 0.0792747
0.3999872 0.0770869
0.4397317 0.0742326
0.4798671 0.0708250
0.5201331 0.0669684
0.5602685 0.0627798
0.6000130 0.0583419
0.6391088 0.0537502
0.6773026 0.0490948
0.7143465 0.0444387
0.7500001 0.0398448
0.7840325 0.0353640
0.8162228 0.0310495
0.8463622 0.0269099
0.8742554 0.0229771
0.8997214 0.0192484
0.9225951 0.0157135
0.9427281 0.0123201
0.9599898 0.0089284
0.9742682 0.0056623
0.9854710 0.0030440
0.9935252 0.0011155
0.9983787 0.0005527
1.0000000 0.0000000
0.0000000 0.0000000
0.0016214 -.0049368
0.0064749 -.0084687
0.0145291 -.0119663
0.0257318 -.0154529
0.0400103 -.0187193
0.0572720 -.0216141
0.0774050 -.0241377
0.1002786 -.0263351
0.1257446 -.0282469
0.1536378 -.0298863
0.1837773 -.0312630
0.2159677 -.0323699
0.2500001 -.0332091
0.2856538 -.0336449
0.3226977 -.0334563
0.3608914 -.0326922
0.3999872 -.0314484
0.4397317 -.0298509
0.4798671 -.0280505
0.5201331 -.0261478
0.5602685 -.0241356
0.6000130 -.0219950
0.6391088 -.0197130
0.6773026 -.0172837
0.7143465 -.0148293
0.7500001 -.0126155
0.7840325 -.0110031
0.8162228 -.0094453
0.8463622 -.0080032
0.8742554 -.0068701
0.8997214 -.0051063
0.9225951 -.0041231
0.9427281 -.0030922
0.9599898 -.0021874
0.9742682 -.0015433
0.9854710 -.0009407
0.9935252 -.0004313
0.9983787 -.0001087
1.0000000 -.0000000
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Polars for DEFIANT CANARD BL145 AIRFOIL (defcnd3-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| defcnd3-il | 50,000 | 9 | 25.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd3-il | 50,000 | 5 | 32.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd3-il | 100,000 | 9 | 44.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd3-il | 100,000 | 5 | 46.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd3-il | 200,000 | 9 | 60.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd3-il | 200,000 | 5 | 61.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd3-il | 500,000 | 9 | 85 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd3-il | 500,000 | 5 | 81.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd3-il | 1,000,000 | 9 | 103.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd3-il | 1,000,000 | 5 | 97.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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