RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL (r1082t-il)
RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL - Roncz 1082T Voyager tip outer aft wing airfoil
| Details | Dat file | Parser | |
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(r1082t-il) RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL Roncz 1082T Voyager tip outer aft wing airfoil Max thickness 16% at 40% chord. Max camber 3% at 40% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL
60.0 60.0
0.0000000 0.0000000
0.0004380 0.0034100
0.0009370 0.0049910
0.0019360 0.0072410
0.0039350 0.0105920
0.0079330 0.0158790
0.0119320 0.0201800
0.0199290 0.0271720
0.0299270 0.0342690
0.0399250 0.0403310
0.0499240 0.0456820
0.0599220 0.0505030
0.0799200 0.0589700
0.0999180 0.0662600
0.1199170 0.0726500
0.1399160 0.0783100
0.1599150 0.0833450
0.1799140 0.0878310
0.1999140 0.0918250
0.2199140 0.0953650
0.2399140 0.0984840
0.2599140 0.1012040
0.2799140 0.1035410
0.2999140 0.1055120
0.3199150 0.1071200
0.3399160 0.1083700
0.3599170 0.1092640
0.3799180 0.1097970
0.3999190 0.1099490
0.4199200 0.1096920
0.4399220 0.1089650
0.4599230 0.1077090
0.4799250 0.1059280
0.4999270 0.1036480
0.5199300 0.1009330
0.5399320 0.0978770
0.5599350 0.0945600
0.5799370 0.0910290
0.5999400 0.0873230
0.6199430 0.0834730
0.6399460 0.0794940
0.6599490 0.0754110
0.6799520 0.0712420
0.6999540 0.0670100
0.7199570 0.0627230
0.7399600 0.0583960
0.7599630 0.0540410
0.7799660 0.0496700
0.7999690 0.0452950
0.8199720 0.0409200
0.8399750 0.0365190
0.8599780 0.0321700
0.8799810 0.0278700
0.8999840 0.0235460
0.9199870 0.0192310
0.9399900 0.0149000
0.9599930 0.0104670
0.9799970 0.0055040
0.9899980 0.0027100
1.0000000 0.0000000
0.0000000 0.0000000
0.0004350 -.0033320
0.0009410 -.0048190
0.0019420 -.0066630
0.0039430 -.0088930
0.0079450 -.0116790
0.0119460 -.0138440
0.0199480 -.0175080
0.0299500 -.0211150
0.0399520 -.0240040
0.0499530 -.0264570
0.0599550 -.0285900
0.0799570 -.0321440
0.0999600 -.0350250
0.1199620 -.0374380
0.1399640 -.0394980
0.1599660 -.0412790
0.1799680 -.0428310
0.1999690 -.0441850
0.2199710 -.0453630
0.2399730 -.0463820
0.2599740 -.0472600
0.2799760 -.0480050
0.2999770 -.0486250
0.3199790 -.0491250
0.3399800 -.0495100
0.3599810 -.0497870
0.3799830 -.0499550
0.3999840 -.0500120
0.4199850 -.0499600
0.4399860 -.0497970
0.4599870 -.0495260
0.4799890 -.0491450
0.4999900 -.0486490
0.5199901 -.0480340
0.5399910 -.0472960
0.5599920 -.0464320
0.5799930 -.0454320
0.5999940 -.0442770
0.6199940 -.0429440
0.6399950 -.0413850
0.6599960 -.0395460
0.6799960 -.0373980
0.6999960 -.0349370
0.7199960 -.0321820
0.7399960 -.0292130
0.7599960 -.0261180
0.7799960 -.0229690
0.7999960 -.0198310
0.8199960 -.0167560
0.8399960 -.0137850
0.8599960 -.0109600
0.8799960 -.0083200
0.8999960 -.0059090
0.9199970 -.0037700
0.9399970 -.0019520
0.9599970 -.0005300
0.9799990 0.0003010
0.9899990 0.0003610
1.0000000 0.0000000
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Polars for RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL (r1082t-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| r1082t-il | 50,000 | 9 | 21.7 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 50,000 | 5 | 16.5 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082t-il | 100,000 | 9 | 34.3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 100,000 | 5 | 38.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082t-il | 200,000 | 9 | 73.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 200,000 | 5 | 69.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082t-il | 500,000 | 9 | 107.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 500,000 | 5 | 101.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082t-il | 1,000,000 | 9 | 135 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082t-il | 1,000,000 | 5 | 122.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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