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NACA 65(4)-221 (naca654221-il)

NACA 65(4)-221 - NACA 65(4)-221 airfoil


Airfoil naca654221-il
Details Dat file Parser  
(naca654221-il) NACA 65(4)-221
NACA 65(4)-221 airfoil
Max thickness 21% at 39.9% chord.
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 65(4)-221
1.00000     0.00000
0.95026     0.00861
0.90052     0.02000
0.85072     0.03270
0.80084     0.04595
0.75088     0.05918
0.70084     0.07195
0.65072     0.08390
0.60054     0.09461
0.55030     0.10372
0.50000     0.11055
0.44967     0.11461
0.39932     0.11570
0.34898     0.11404
0.29865     0.11007
0.24834     0.10381
0.19808     0.09514
0.14787     0.08370
0.09778     0.06865
0.07280     0.05918
0.04791     0.04783
0.02314     0.03335
0.01090     0.02402
0.00608     0.01902
0.00372     0.01567
0.00000     0.00000
0.00628     -0.01467
0.00892     -0.01762
0.01410     -0.02188
0.02684     -0.02963
0.05209     -0.04151
0.07720     -0.05070
0.10222     -0.05831
0.15213     -0.07024
0.20192     -0.07922
0.25166     -0.08591
0.30135     -0.09063
0.35102     -0.09344
0.40068     -0.09428
0.45033     -0.09271
0.50000     -0.08849
0.54970     -0.08182
0.59946     -0.07319
0.64928     -0.06330
0.69916     -0.05251
0.74912     -0.04128
0.79916     -0.03003
0.84928     -0.01924
0.89948     -0.00966
0.94974     -0.00229
1.00000     0.00000
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Selig format dat file

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Polars for NACA 65(4)-221 (naca654221-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca654221-il50,000915.7 at α=13.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca654221-il50,000512.4 at α=12.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca654221-il100,000921.3 at α=11.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca654221-il100,000520.7 at α=10.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca654221-il200,000950.2 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   naca654221-il200,000552.6 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca654221-il500,000986.2 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca654221-il500,000578.6 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca654221-il1,000,0009105.8 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca654221-il1,000,000591.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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