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AS5045 (15%) (as5045-il)

AS5045 (15%) - AS5045 airfoil Ashok Gopalarathnam/Selig 15% airfoil


Airfoil as5045-il
Details Dat file Parser  
(as5045-il) AS5045 (15%)
AS5045 airfoil Ashok Gopalarathnam/Selig 15% airfoil
Max thickness 15% at 37.5% chord.
Max camber 1% at 27.2% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
AS5045 (15%)
1.0000 .00125
.99810 .00168
.99262 .00289
.98385 .00461
.97186 .00684
.95690 .00935
.93892 .01196
.91780 .01477
.89367 .01788
.86673 .02140
.83721 .02541
.80536 .03000
.77153 .03526
.73615 .04132
.69982 .04811
.66317 .05543
.62680 .06283
.59096 .06923
.55516 .07433
.51913 .07831
.48292 .08123
.44664 .08325
.41052 .08449
.37479 .08499
.33967 .08478
.30537 .08387
.27211 .08229
.24008 .08005
.20946 .07717
.18043 .07367
.15315 .06959
.12777 .06496
.10446 .05981
.08330 .05416
.06436 .04806
.04778 .04161
.03361 .03483
.02185 .02787
.01263 .02078
.00593 .01366
.00173 .00668
.00000 .00008
.00109 -.00530
.00587 -.00990
.01434 -.01476
.02592 -.01980
.04036 -.02496
.05747 -.03017
.07703 -.03536
.09884 -.04037
.12277 -.04507
.14872 -.04937
.17657 -.05321
.20618 -.05657
.23735 -.05943
.26989 -.06175
.30359 -.06349
.33826 -.06458
.37369 -.06501
.40968 -.06473
.44597 -.06373
.48229 -.06181
.51861 -.05884
.55478 -.05472
.59103 -.04922
.62759 -.04265
.66456 -.03535
.70215 -.02815
.73949 -.02165
.77577 -.01601
.81059 -.01127
.84351 -.00739
.87413 -.00440
.90208 -.00224
.92701 -.00085
.94861 -.00008
.96671 .00018 
.98110 .00002
.99155 -.00045
.99786 -.00099
1.0000 -.00125
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 AS5045 (15%) (as5045-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   as5045-il50,000930 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   as5045-il50,000529.2 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   as5045-il100,000944 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   as5045-il100,000543.5 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   as5045-il200,000959.5 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   as5045-il200,000556.6 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   as5045-il500,000979.4 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   as5045-il500,000570.3 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   as5045-il1,000,000992.5 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   as5045-il1,000,000581.9 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
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