Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

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


Airfoil r1082t-il
Details Dat file Parser  
(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
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

FX 78-K-161PreviewDetails
AH 93-157PreviewDetails
EPPLER 682 AIRFOILPreviewDetails
AH 94-156PreviewDetails
AH 93-156PreviewDetails
AH 83-159PreviewDetails
EPPLER 642 AIRFOILPreviewDetails
FX 61-163 AIRFOILPreviewDetails
MRC-20PreviewDetails
FX 61-168 AIRFOILPreviewDetails

Polars for RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL (r1082t-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   r1082t-il50,000921.7 at α=12.75°Mach=0 Ncrit=9Xfoil predictionDetails
   r1082t-il50,000516.5 at α=12.5°Mach=0 Ncrit=5Xfoil predictionDetails
   r1082t-il100,000934.3 at α=11.25°Mach=0 Ncrit=9Xfoil predictionDetails
   r1082t-il100,000538.2 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   r1082t-il200,000973.2 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   r1082t-il200,000569.4 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   r1082t-il500,0009107.6 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   r1082t-il500,0005101.6 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   r1082t-il1,000,0009135 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   r1082t-il1,000,0005122.4 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit