RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL (r1080-il)
RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL - Roncz 1080 Voyager inner aft wing airfoil
| Details | Dat file | Parser | |
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(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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Polars for RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL (r1080-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| r1080-il | 50,000 | 9 | 5.8 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 50,000 | 5 | 13.3 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1080-il | 100,000 | 9 | 28 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 100,000 | 5 | 22.9 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1080-il | 200,000 | 9 | 55.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 200,000 | 5 | 55.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1080-il | 500,000 | 9 | 106.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 500,000 | 5 | 102.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1080-il | 1,000,000 | 9 | 139.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 1,000,000 | 5 | 127 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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