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S7075 (9%) (s7075-il)

S7075 (9%) - Selig S7075 low Reynolds number airfoil


Airfoil s7075-il
Details Dat file Parser  
(s7075-il) S7075 (9%)
Selig S7075 low Reynolds number airfoil
Max thickness 9% at 29% chord.
Max camber 2.8% at 46.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S7075 (9%)
       1.00000     0.00000
       0.99811     0.00030
       0.99262     0.00130
       0.98384     0.00301
       0.97189     0.00532
       0.95689     0.00825
       0.93906     0.01183
       0.91865     0.01599
       0.89590     0.02064
       0.87105     0.02565
       0.84435     0.03084
       0.81590     0.03603
       0.78585     0.04114
       0.75438     0.04596
       0.72152     0.05039
       0.68736     0.05452
       0.65213     0.05833
       0.61605     0.06181
       0.57936     0.06492
       0.54228     0.06762
       0.50502     0.06988
       0.46782     0.07165
       0.43086     0.07290
       0.39436     0.07362
       0.35853     0.07377
       0.32355     0.07334
       0.28961     0.07232
       0.25690     0.07072
       0.22556     0.06854
       0.19578     0.06579
       0.16769     0.06249
       0.14143     0.05868
       0.11714     0.05438
       0.09490     0.04963
       0.07485     0.04451
       0.05704     0.03906
       0.04155     0.03336
       0.02846     0.02751
       0.01783     0.02158
       0.00974     0.01572
       0.00426     0.00983
       0.00112     0.00396
       0.00012    -0.00127
       0.00205    -0.00532
       0.00740    -0.00861
       0.01586    -0.01154
       0.02736    -0.01403
       0.04182    -0.01616
       0.05915    -0.01785
       0.07927    -0.01912
       0.10208    -0.01997
       0.12746    -0.02041
       0.15527    -0.02049
       0.18536    -0.02022
       0.21756    -0.01965
       0.25167    -0.01880
       0.28749    -0.01774
       0.32478    -0.01649
       0.36331    -0.01510
       0.40283    -0.01360
       0.44306    -0.01205
       0.48375    -0.01047
       0.52460    -0.00889
       0.56534    -0.00734
       0.60568    -0.00584
       0.64532    -0.00438
       0.68397    -0.00291
       0.72149    -0.00140
       0.75769     0.00009
       0.79235     0.00160
       0.82543     0.00301
       0.85679     0.00399
       0.88582     0.00420
       0.91190     0.00378
       0.93478     0.00312
       0.95435     0.00237
       0.97053     0.00163
       0.98322     0.00099
       0.99243     0.00051
       0.99808     0.00016
       1.00000     0.00000
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Polars for S7075 (9%) (s7075-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s7075-il50,000938.8 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s7075-il50,000540.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   s7075-il100,000959.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s7075-il100,000557.7 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s7075-il200,000981.3 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   s7075-il200,000574 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s7075-il500,0009108 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s7075-il500,000591.6 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s7075-il1,000,0009123 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s7075-il1,000,0005101.8 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
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