DEFIANT CANARD BL110 AIRFOIL (defcnd2-il)
DEFIANT CANARD BL110 AIRFOIL - Rutan DEFIANT canard BL110 airfoil
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(defcnd2-il) DEFIANT CANARD BL110 AIRFOIL Rutan DEFIANT canard BL110 airfoil Max thickness 14.7% at 28.6% chord. Max camber 3.8% at 28.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
DEFIANT CANARD BL110 AIRFOIL
40.0 40.0
0.0000000 0.0000000
0.0016214 0.0053580
0.0064749 0.0140194
0.0145291 0.0237353
0.0257318 0.0340204
0.0400103 0.0445357
0.0572720 0.0549526
0.0774050 0.0651389
0.1002786 0.0749930
0.1257446 0.0843638
0.1536378 0.0930201
0.1837773 0.1005530
0.2159677 0.1054206
0.2500001 0.1093530
0.2856538 0.1117825
0.3226977 0.1114109
0.3608914 0.1106019
0.3999872 0.1090801
0.4397317 0.1060267
0.4798671 0.1017465
0.5201331 0.0968208
0.5602685 0.0916715
0.6000130 0.0858060
0.6391088 0.0792232
0.6773026 0.0719772
0.7143465 0.0641511
0.7500001 0.0560973
0.7840325 0.0484034
0.8162228 0.0412098
0.8463622 0.0344614
0.8742554 0.0282001
0.8997214 0.0224860
0.9225951 0.0173575
0.9427281 0.0128440
0.9599898 0.0089735
0.9742682 0.0057713
0.9854710 0.0032588
0.9935252 0.0014522
0.9983787 0.0003637
1.0000000 0.0000000
0.0000000 0.0000000
0.0016214 -.0060013
0.0064749 -.0105925
0.0145291 -.0142349
0.0257318 -.0179035
0.0400103 -.0212647
0.0572720 -.0241388
0.0774050 -.0267026
0.1002786 -.0288855
0.1257446 -.0307166
0.1536378 -.0322314
0.1837773 -.0334527
0.2159677 -.0344085
0.2500001 -.0351050
0.2856538 -.0355493
0.3226977 -.0357463
0.3608914 -.0356932
0.3999872 -.0353934
0.4397317 -.0348249
0.4798671 -.0339652
0.5201331 -.0328013
0.5602685 -.0312835
0.6000130 -.0293381
0.6391088 -.0268735
0.6773026 -.0240072
0.7143465 -.0212376
0.7500001 -.0185965
0.7840325 -.0160612
0.8162228 -.0136681
0.8463622 -.0114267
0.8742554 -.0093522
0.8997214 -.0074585
0.9225951 -.0057569
0.9427281 -.0042592
0.9599898 -.0029757
0.9742682 -.0019142
0.9854710 -.0010808
0.9935252 -.0004812
0.9983787 -.0001204
1.0000000 -.0000000
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Polars for DEFIANT CANARD BL110 AIRFOIL (defcnd2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| defcnd2-il | 50,000 | 9 | 8.4 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd2-il | 50,000 | 5 | 28.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd2-il | 100,000 | 9 | 41.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd2-il | 100,000 | 5 | 47.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd2-il | 200,000 | 9 | 64.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd2-il | 200,000 | 5 | 64.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd2-il | 500,000 | 9 | 89.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd2-il | 500,000 | 5 | 89.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd2-il | 1,000,000 | 9 | 117.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd2-il | 1,000,000 | 5 | 115 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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