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RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il)

RONCZ 1046 VOYAGER CANARD AIRFOIL - Roncz 1046 Voyager canard airfoil


Airfoil r1046-il
Details Dat file Parser  
(r1046-il) RONCZ 1046 VOYAGER CANARD AIRFOIL
Roncz 1046 Voyager canard airfoil
Max thickness 18.1% at 38% chord.
Max camber 6.7% at 42% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 RONCZ 1046 VOYAGER CANARD AIRFOIL
      60.0      60.0

 0.0000000 0.0000000
 0.0005000 0.0045870
 0.0010000 0.0066830
 0.0020000 0.0097700
 0.0040000 0.0144120
 0.0080000 0.0215790
 0.0120000 0.0273640
 0.0200000 0.0368300
 0.0300000 0.0465140
 0.0400000 0.0548230
 0.0500000 0.0622400
 0.0600000 0.0689900
 0.0800000 0.0809920
 0.1000000 0.0914590
 0.1200000 0.1007280
 0.1400000 0.1090120
 0.1600000 0.1164560
 0.1800000 0.1231430
 0.2000000 0.1291370
 0.2200000 0.1344910
 0.2400000 0.1392440
 0.2600000 0.1434220
 0.2800000 0.1470410
 0.3000000 0.1501590
 0.3200000 0.1526220
 0.3400000 0.1545670
 0.3600000 0.1559150
 0.3800000 0.1566330
 0.4000000 0.1566920
 0.4200000 0.1560720
 0.4400000 0.1547430
 0.4600000 0.1526720
 0.4800000 0.1498610
 0.5000000 0.1463530
 0.5200000 0.1422270
 0.5400000 0.1376150
 0.5600000 0.1326400
 0.5800000 0.1273720
 0.6000000 0.1218700
 0.6200000 0.1161750
 0.6400000 0.1103240
 0.6600000 0.1043510
 0.6800000 0.0982870
 0.7000000 0.0921600
 0.7200000 0.0859900
 0.7400000 0.0797940
 0.7600000 0.0735930
 0.7800000 0.0674040
 0.8000000 0.0612360
 0.8200000 0.0550960
 0.8400000 0.0489890
 0.8600000 0.0429220
 0.8800000 0.0368680
 0.9000000 0.0307700
 0.9200000 0.0245140
 0.9400000 0.0180230
 0.9600000 0.0114090
 0.9800000 0.0050950
 0.9900000 0.0022820
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0005000 -.0040980
 0.0010000 -.0054290
 0.0020000 -.0070480
 0.0040000 -.0090610
 0.0080000 -.0116230
 0.0120000 -.0135030
 0.0200000 -.0161840
 0.0300000 -.0185770
 0.0400000 -.0204090
 0.0500000 -.0218440
 0.0600000 -.0229850
 0.0800000 -.0246950
 0.1000000 -.0258920
 0.1200000 -.0267310
 0.1400000 -.0273100
 0.1600000 -.0276890
 0.1800000 -.0278870
 0.2000000 -.0279260
 0.2200000 -.0278350
 0.2400000 -.0276370
 0.2600000 -.0273490
 0.2800000 -.0269850
 0.3000000 -.0265570
 0.3200000 -.0260750
 0.3400000 -.0255440
 0.3600000 -.0249630
 0.3800000 -.0243280
 0.4000000 -.0236370
 0.4200000 -.0228870
 0.4400000 -.0220750
 0.4600000 -.0212060
 0.4800000 -.0202810
 0.5000000 -.0193120
 0.5200000 -.0183120
 0.5400000 -.0172990
 0.5600000 -.0162820
 0.5800000 -.0152680
 0.6000000 -.0142650
 0.6200000 -.0132750
 0.6400000 -.0123000
 0.6600000 -.0113440
 0.6800000 -.0104110
 0.7000000 -.0095050
 0.7200000 -.0086310
 0.7400000 -.0077900
 0.7600000 -.0069830
 0.7800000 -.0062100
 0.8000000 -.0054710
 0.8200000 -.0047660
 0.8400000 -.0041000
 0.8600000 -.0034670
 0.8800000 -.0028510
 0.9000000 -.0022210
 0.9200000 -.0015300
 0.9400000 -.0007810
 0.9600000 -.0000620
 0.9800000 0.0003960
 0.9900000 0.0003840
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   r1046-il50,00094.4 at α=12.25°Mach=0 Ncrit=9Xfoil predictionDetails
   r1046-il50,00056.9 at α=12.5°Mach=0 Ncrit=5Xfoil predictionDetails
   r1046-il100,000913 at α=19°Mach=0 Ncrit=9Xfoil predictionDetails
   r1046-il100,000520.5 at α=1°Mach=0 Ncrit=5Xfoil predictionDetails
   r1046-il200,000926.5 at α=1.25°Mach=0 Ncrit=9Xfoil predictionDetails
   r1046-il200,000554.2 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   r1046-il500,0009101.4 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   r1046-il500,0005108.1 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   r1046-il1,000,0009148.8 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   r1046-il1,000,0005149.6 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
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