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AS5048 (18%) (as5048-il)

AS5048 (18%) - AS5048 airfoil Ashok Gopalarathnam/Selig 18% airfoil


Airfoil as5048-il
Details Dat file Parser  
(as5048-il) AS5048 (18%)
AS5048 airfoil Ashok Gopalarathnam/Selig 18% airfoil
Max thickness 18% at 38.3% chord.
Max camber 0.8% at 77.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AS5048 (18%)
1.0000 .00150  
.99795 .00261 
.99261 .00526 
.98429 .00834  
.97271 .01198  
.95837 .01595 
.94112 .01990  
.92072 .02396  
.89732 .02822  
.87111 .03280  
.84231 .03773  
.81114 .04314 
.77793 .04906 
.74304 .05563  
.70708 .06281 
.67063 .07045 
.63428 .07812 
.59851 .08492 
.56284 .09044  
.52688 .09468  
.49071 .09776  
.45445 .09986  
.41832 .10106  
.38251 .10140  
.34725 .10094  
.31275 .09972
.27924 .09776
.24695 .09505
.21603 .09161
.18663 .08747
.15891 .08271
.13309 .07739
.10936 .07152
.08785 .06502
.06852 .05792
.05146 .05041 
.03674 .04254 
.02438 .03444
.01454 .02625
.00721 .01805
.00240 .01003
.00014 .00239
.00041 -.00424
.00441 -.00990 
.01248 -.01556
.02377 -.02150
.03798 -.02765
.05482 -.03390
.07412 -.04008
.09574 -.04606
.11951 -.05174
.14532 -.05699
.17306 -.06177
.20256 -.06603
.23366 -.06976
.26613 -.07290
.29980 -.07540
.33444 -.07722
.36986 -.07831
.40583 -.07864
.44212 -.07817
.47846 -.07674
.51476 -.07422
.55088 -.07046
.58702 -.06529
.62334 -.05893
.65996 -.05165  
.69717 -.04405
.73423 -.03698
.77029 -.03077
.80489 -.02531
.83759 -.02055
.86800 -.01650
.89575 -.01309
.92048 -.01021
.94185 -.00763
.96018 -.00471
.97608 -.00204
.98886 -.00090
.99713 -.00109
1.0000 -.00149
http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/
Dat file parser warnings
  • Line 83 - Invalid characters : http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/
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Polars for AS5048 (18%) (as5048-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   as5048-il50,000925 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   as5048-il50,000523.6 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   as5048-il100,000941.2 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   as5048-il100,000540.4 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   as5048-il200,000959.9 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   as5048-il200,000556.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   as5048-il500,000981.4 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   as5048-il500,000571 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   as5048-il1,000,000996.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   as5048-il1,000,000579.8 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
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