Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

DEFIANT CANARD BL110 AIRFOIL (defcnd2-il)

DEFIANT CANARD BL110 AIRFOIL - Rutan DEFIANT canard BL110 airfoil


Airfoil defcnd2-il
Details Dat file Parser  
(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
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

USA 45 AIRFOILPreviewDetails
EPPLER 343 AIRFOILPreviewDetails
Eiffel 371 (Monge)PreviewDetails
EPPLER 344 AIRFOILPreviewDetails
WORTMANN FX 77-W-153 AIRFOILPreviewDetails
STRAND AIRFOILPreviewDetails
EPPLER 342 AIRFOILPreviewDetails
FX 63-145 AIRFOILPreviewDetails
FX 61-147 AIRFOILPreviewDetails
AH 80-140PreviewDetails

Polars for DEFIANT CANARD BL110 AIRFOIL (defcnd2-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   defcnd2-il50,00098.4 at α=0.75°Mach=0 Ncrit=9Xfoil predictionDetails
   defcnd2-il50,000528.3 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   defcnd2-il100,000941.7 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   defcnd2-il100,000547.9 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   defcnd2-il200,000964.5 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   defcnd2-il200,000564.5 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   defcnd2-il500,000989.6 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   defcnd2-il500,000589.6 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   defcnd2-il1,000,0009117.2 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   defcnd2-il1,000,0005115 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit