DEFIANT CANARD BL20 AIRFOIL (defcnd1-il)
DEFIANT CANARD BL20 AIRFOIL - Rutan DEFIANT canard BL20 airfoil
| Details | Dat file | Parser | |
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(defcnd1-il) DEFIANT CANARD BL20 AIRFOIL Rutan DEFIANT canard BL20 airfoil Max thickness 20.9% at 28.6% chord. Max camber 4.5% at 36.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
DEFIANT CANARD BL20 AIRFOIL
40.0 40.0
0.0000000 0.0000000
0.0016214 0.0091471
0.0064749 0.0215180
0.0145291 0.0347701
0.0257318 0.0481265
0.0400103 0.0616766
0.0572720 0.0756057
0.0774050 0.0892795
0.1002786 0.1021710
0.1257446 0.1138956
0.1536378 0.1241680
0.1837773 0.1327803
0.2159677 0.1395810
0.2500001 0.1444585
0.2856538 0.1473266
0.3226977 0.1481118
0.3608914 0.1467474
0.3999872 0.1432367
0.4397317 0.1376932
0.4798671 0.1303391
0.5201331 0.1214931
0.5602685 0.1115495
0.6000130 0.1009499
0.6391088 0.0901477
0.6773026 0.0795915
0.7143465 0.0696557
0.7500001 0.0606542
0.7840325 0.0524394
0.8162228 0.0446150
0.8463622 0.0372980
0.8742554 0.0305273
0.8997214 0.0243445
0.9225951 0.0187918
0.9427281 0.0139041
0.9599898 0.0097130
0.9742682 0.0062466
0.9854710 0.0035270
0.9935252 0.0015717
0.9983787 0.0003936
1.0000000 0.0000000
0.0000000 0.0000000
0.0016214 -.0113422
0.0064749 -.0188655
0.0145291 -.0262204
0.0257318 -.0336067
0.0400103 -.0406294
0.0572720 -.0469106
0.0774050 -.0521279
0.1002786 -.0558482
0.1257446 -.0584558
0.1536378 -.0605590
0.1837773 -.0620560
0.2159677 -.0628278
0.2500001 -.0627871
0.2856538 -.0618809
0.3226977 -.0600925
0.3608914 -.0574578
0.3999872 -.0541306
0.4397317 -.0503338
0.4798671 -.0463273
0.5201331 -.0423900
0.5602685 -.0387560
0.6000130 -.0353050
0.6391088 -.0318592
0.6773026 -.0284750
0.7143465 -.0252070
0.7500001 -.0220635
0.7840325 -.0190599
0.8162228 -.0162183
0.8463622 -.0135584
0.8742554 -.0110970
0.8997214 -.0088498
0.9225951 -.0068314
0.9427281 -.0050547
0.9599898 -.0035313
0.9742682 -.0022711
0.9854710 -.0012823
0.9935252 -.0005715
0.9983787 -.0001431
1.0000000 -.0000000
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Polars for DEFIANT CANARD BL20 AIRFOIL (defcnd1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| defcnd1-il | 50,000 | 9 | 3 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd1-il | 50,000 | 5 | 6.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd1-il | 100,000 | 9 | 4.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd1-il | 100,000 | 5 | 32.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd1-il | 200,000 | 9 | 52.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd1-il | 200,000 | 5 | 60.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd1-il | 500,000 | 9 | 93.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd1-il | 500,000 | 5 | 92.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| defcnd1-il | 1,000,000 | 9 | 124.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| defcnd1-il | 1,000,000 | 5 | 116.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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