Airfoil Tools
Search 1638 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)
 

RUTAN WING AIRFOIL (amsoil2-il)

RUTAN WING AIRFOIL - Rutan AMSOIL racer wing airfoil


Airfoil amsoil2-il
Details Dat file Parser  
(amsoil2-il) RUTAN WING AIRFOIL
Rutan AMSOIL racer wing airfoil
Max thickness 11.8% at 39% chord.
Max camber 1% at 48% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
 
 RUTAN WING AIRFOIL
38.        38.
 
 0.00000   0.00000
  .00288    .01168
  .00575    .01600
  .01151    .02158
  .02998    .03159
  .05996    .04022
  .08994    .04581
  .11992    .05001
  .14990    .05346
  .17988    .05645
  .20986    .05910
  .23984    .06146
  .26982    .06347
  .29980    .06514
  .32978    .06646
  .35977    .06744
  .38975    .06802
  .41973    .06819
  .44971    .06790
  .47969    .06721
  .50967    .06600
  .53965    .06433
  .56963    .06226
  .59961    .05967
  .62959    .05668
  .65957    .05329
  .68955    .04949
  .71953    .04534
  .74951    .04097
  .77949    .03631
  .80947    .03148
  .83945    .02659
  .86943    .02164
  .89941    .01675
  .92939    .01203
  .95937    .00760
  .98935    .00357
 1.00000    .00224
 
 0.00000   0.00000
  .00288   -.01145
  .00575   -.01554
  .01151   -.02072
  .02998   -.02929
  .05996   -.03585
  .08994   -.03942
  .11992   -.04183
  .14990   -.04362
  .17988   -.04506
  .20986   -.04627
  .23984   -.04730
  .26982   -.04816
  .29980   -.04885
  .32978   -.04932
  .35977   -.04960
  .38975   -.04960
  .41973   -.04932
  .44971   -.04874
  .47969   -.04782
  .50967   -.04661
  .53965   -.04511
  .56963   -.04322
  .59961   -.04109
  .62959   -.03861
  .65957   -.03585
  .68955   -.03286
  .71953   -.02969
  .74951   -.02641
  .77949   -.02296
  .80947   -.01951
  .83945   -.01611
  .86943   -.01283
  .89941   -.00972
  .92939   -.00696
  .95937   -.00460
  .98935   -.00276
 1.00000   -.00224
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

NACA 64(1)-212PreviewDetails
NACA 65(1)-212PreviewDetails
NACA 64(1)-112PreviewDetails
NACA 65(1)-212 a=0.6PreviewDetails
HQ 1.0/12 AIRFOILPreviewDetails
R140 (original)PreviewDetails
HQ 1.5/12 AIRFOILPreviewDetails
MH 27 11.99%PreviewDetails
LOCKHEED C-141 BL426.57 AIRFOILPreviewDetails
NACA 66(1)-212PreviewDetails

Polars for RUTAN WING AIRFOIL (amsoil2-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   amsoil2-il50,000925.9 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   amsoil2-il50,000525.3 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
   amsoil2-il100,000938.7 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   amsoil2-il100,000535.4 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   amsoil2-il200,000948.9 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   amsoil2-il200,000542.8 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   amsoil2-il500,000956.9 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   amsoil2-il500,000561.7 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   amsoil2-il1,000,000974.9 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   amsoil2-il1,000,000577.4 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit