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RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL (r1082-il)

RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL - Roncz 1082 Voyager root outer aft wing airfoil


Airfoil r1082-il
Details Dat file Parser  
(r1082-il) RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL
Roncz 1082 Voyager root outer aft wing airfoil
Max thickness 18% at 40% chord.
Max camber 3.4% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL
      60.0      60.0

 0.0000000 0.0000000
 0.0004520 0.0039110
 0.0009510 0.0056950
 0.0019510 0.0082470
 0.0039490 0.0120530
 0.0079480 0.0180080
 0.0119460 0.0228400
 0.0199440 0.0307030
 0.0299420 0.0386930
 0.0399400 0.0455120
 0.0499390 0.0515320
 0.0599370 0.0569570
 0.0799350 0.0664820
 0.0999330 0.0746830
 0.1199320 0.0818710
 0.1399310 0.0882370
 0.1599300 0.0938990
 0.1799290 0.0989470
 0.1999290 0.1034390
 0.2199280 0.1074190
 0.2399280 0.1109260
 0.2599280 0.1139830
 0.2799280 0.1166120
 0.2999280 0.1188270
 0.3199290 0.1206340
 0.3399290 0.1220380
 0.3599300 0.1230420
 0.3799310 0.1236370
 0.3999310 0.1238070
 0.4199330 0.1235150
 0.4399340 0.1226940
 0.4599350 0.1212780
 0.4799370 0.1192710
 0.4999380 0.1167020
 0.5199401 0.1136460
 0.5399430 0.1102040
 0.5599450 0.1064680
 0.5799470 0.1024930
 0.5999490 0.0983210
 0.6199520 0.0939820
 0.6399540 0.0895040
 0.6599560 0.0849060
 0.6799590 0.0802120
 0.6999610 0.0754460
 0.7199640 0.0706200
 0.7399660 0.0657480
 0.7599690 0.0608440
 0.7799710 0.0559240
 0.7999740 0.0509970
 0.8199770 0.0460700
 0.8399790 0.0411800
 0.8599820 0.0362530
 0.8799840 0.0313740
 0.8999870 0.0265100
 0.9199890 0.0216500
 0.9399920 0.0167760
 0.9599940 0.0117840
 0.9799970 0.0061970
 0.9899990 0.0030520
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0004540 -.0037650
 0.0009550 -.0053450
 0.0019560 -.0073440
 0.0039570 -.0098130
 0.0079580 -.0129920
 0.0119590 -.0154700
 0.0199600 -.0195830
 0.0299620 -.0236230
 0.0399640 -.0268850
 0.0499650 -.0296500
 0.0599660 -.0320470
 0.0799690 -.0360490
 0.0999710 -.0392940
 0.1199730 -.0420120
 0.1399740 -.0443340
 0.1599760 -.0463420
 0.1799770 -.0480900
 0.1999790 -.0496150
 0.2199800 -.0509430
 0.2399810 -.0520930
 0.2599830 -.0530820
 0.2799840 -.0539250
 0.2999850 -.0546250
 0.3199860 -.0551910
 0.3399870 -.0556270
 0.3599880 -.0559420
 0.3799890 -.0561320
 0.3999900 -.0562000
 0.4199910 -.0561430
 0.4399920 -.0559630
 0.4599930 -.0556610
 0.4799940 -.0552340
 0.4999940 -.0546790
 0.5199950 -.0539890
 0.5399960 -.0531610
 0.5599960 -.0521910
 0.5799970 -.0510690
 0.5999980 -.0497720
 0.6199980 -.0482750
 0.6399980 -.0465240
 0.6599990 -.0444570
 0.6799990 -.0420410
 0.6999990 -.0392750
 0.7199990 -.0361780
 0.7399990 -.0328390
 0.7599980 -.0293590
 0.7799980 -.0258180
 0.7999980 -.0222890
 0.8199980 -.0188310
 0.8399980 -.0154910
 0.8599970 -.0123150
 0.8799970 -.0093480
 0.8999980 -.0066370
 0.9199980 -.0042310
 0.9399980 -.0021880
 0.9599980 -.0005910
 0.9799990 0.0003410
 0.9899990 0.0004080
 1.0000000 0.0000000
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Lednicer format dat file
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Polars for RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL (r1082-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   r1082-il50,00094.2 at α=12°Mach=0 Ncrit=9Xfoil predictionDetails
   r1082-il50,000512.1 at α=14.75°Mach=0 Ncrit=5Xfoil predictionDetails
   r1082-il100,000925.4 at α=13.5°Mach=0 Ncrit=9Xfoil predictionDetails
   r1082-il100,000521.5 at α=12.25°Mach=0 Ncrit=5Xfoil predictionDetails
   r1082-il200,000960.9 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   r1082-il200,000561.2 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   r1082-il500,0009105.1 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   r1082-il500,0005102.2 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   r1082-il1,000,0009136.8 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   r1082-il1,000,0005127.1 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
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