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RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL (r1080-il)

RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL - Roncz 1080 Voyager inner aft wing airfoil


Airfoil r1080-il
Details Dat file Parser  
(r1080-il) RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL
Roncz 1080 Voyager inner aft wing airfoil
Max thickness 18% at 40% chord.
Max camber 3.3% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL
      60.0      60.0
 
 0.0000000 0.0000000
 0.0004700 0.0042380
 0.0009700 0.0061470
 0.0019700 0.0088730
 0.0039700 0.0128790
 0.0079700 0.0190450
 0.0119700 0.0240120
 0.0199700 0.0319950
 0.0299690 0.0399850
 0.0399690 0.0467270
 0.0499700 0.0526460
 0.0599700 0.0579640
 0.0799700 0.0672600
 0.0999700 0.0752170
 0.1199700 0.0821560
 0.1399710 0.0882740
 0.1599710 0.0937040
 0.1799710 0.0985400
 0.1999720 0.1028450
 0.2199720 0.1066690
 0.2399730 0.1100450
 0.2599730 0.1130000
 0.2799740 0.1155520
 0.2999740 0.1177200
 0.3199750 0.1195140
 0.3399750 0.1209390
 0.3599760 0.1219930
 0.3799760 0.1226770
 0.3999770 0.1229880
 0.4199770 0.1229180
 0.4399780 0.1224370
 0.4599790 0.1215050
 0.4799790 0.1200390
 0.4999800 0.1179520
 0.5199811 0.1152300
 0.5399810 0.1119090
 0.5599820 0.1080670
 0.5799830 0.1038400
 0.5999840 0.0993460
 0.6199850 0.0946520
 0.6399850 0.0898070
 0.6599860 0.0848480
 0.6799870 0.0798030
 0.6999880 0.0747010
 0.7199890 0.0695620
 0.7399890 0.0644090
 0.7599900 0.0592600
 0.7799910 0.0541300
 0.7999920 0.0490340
 0.8199930 0.0439800
 0.8399940 0.0389850
 0.8599940 0.0340560
 0.8799950 0.0292020
 0.8999960 0.0244200
 0.9199970 0.0197130
 0.9399980 0.0150680
 0.9599980 0.0104020
 0.9799990 0.0053380
 0.9900000 0.0025910
 1.0000000 0.0000000
 
 0.0000000 0.0000000
 0.0004650 -.0038000
 0.0009710 -.0052840
 0.0019710 -.0071130
 0.0039710 -.0094410
 0.0079710 -.0125540
 0.0119710 -.0150270
 0.0199720 -.0190310
 0.0299720 -.0229880
 0.0399730 -.0262390
 0.0499730 -.0290090
 0.0599740 -.0314150
 0.0799740 -.0354610
 0.0999750 -.0387780
 0.1199760 -.0415760
 0.1399760 -.0439850
 0.1599770 -.0460850
 0.1799780 -.0479250
 0.1999780 -.0495410
 0.2199790 -.0509590
 0.2399800 -.0521970
 0.2599800 -.0532740
 0.2799810 -.0542010
 0.2999820 -.0549840
 0.3199820 -.0556320
 0.3399830 -.0561500
 0.3599840 -.0565440
 0.3799840 -.0568150
 0.3999850 -.0569660
 0.4199850 -.0569950
 0.4399860 -.0569030
 0.4599870 -.0566880
 0.4799870 -.0563450
 0.4999880 -.0558660
 0.5199880 -.0552410
 0.5399890 -.0544670
 0.5599890 -.0535360
 0.5799900 -.0524370
 0.5999900 -.0511490
 0.6199910 -.0496450
 0.6399910 -.0478650
 0.6599920 -.0457450
 0.6799920 -.0432620
 0.6999930 -.0404260
 0.7199930 -.0372710
 0.7399940 -.0338990
 0.7599940 -.0304120
 0.7799950 -.0268830
 0.7999950 -.0233780
 0.8199960 -.0199460
 0.8399960 -.0166270
 0.8599960 -.0134610
 0.8799970 -.0104880
 0.8999970 -.0077460
 0.9199980 -.0052700
 0.9399980 -.0030940
 0.9599990 -.0012860
 0.9799990 -.0000510
 0.9900000 0.0001990
 1.0000000 0.0000000
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Lednicer format dat file
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Polars for RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL (r1080-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   r1080-il50,00095.8 at α=13.25°Mach=0 Ncrit=9Xfoil predictionDetails
   r1080-il50,000513.3 at α=13.75°Mach=0 Ncrit=5Xfoil predictionDetails
   r1080-il100,000928 at α=12.5°Mach=0 Ncrit=9Xfoil predictionDetails
   r1080-il100,000522.9 at α=11.75°Mach=0 Ncrit=5Xfoil predictionDetails
   r1080-il200,000955.7 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   r1080-il200,000555.7 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   r1080-il500,0009106.5 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   r1080-il500,0005102.2 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   r1080-il1,000,0009139.3 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   r1080-il1,000,0005127 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
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