RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il)
RONCZ 1046 VOYAGER CANARD AIRFOIL - Roncz 1046 Voyager canard airfoil
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(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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Polars for RONCZ 1046 VOYAGER CANARD AIRFOIL (r1046-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| r1046-il | 50,000 | 9 | 4.4 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1046-il | 50,000 | 5 | 6.9 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1046-il | 100,000 | 9 | 13 at α=19° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1046-il | 100,000 | 5 | 20.5 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1046-il | 200,000 | 9 | 26.5 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1046-il | 200,000 | 5 | 54.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1046-il | 500,000 | 9 | 101.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1046-il | 500,000 | 5 | 108.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1046-il | 1,000,000 | 9 | 148.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1046-il | 1,000,000 | 5 | 149.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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