Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S8037 (16%) (s8037-il)

S8037 (16%) - Selig S8037 low Reynolds number airfoil


Airfoil s8037-il
Details Dat file Parser  
(s8037-il) S8037 (16%)
Selig S8037 low Reynolds number airfoil
Max thickness 16% at 33.5% chord.
Max camber 1.9% at 40.4% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S8037 (16%)
       1.00000     0.00000
       0.99758     0.00043
       0.99089     0.00205
       0.98084     0.00478
       0.96782     0.00814
       0.95171     0.01178
       0.93244     0.01580
       0.91019     0.02034
       0.88520     0.02543
       0.85776     0.03105
       0.82813     0.03716
       0.79662     0.04370
       0.76352     0.05059
       0.72913     0.05772
       0.69378     0.06496
       0.65776     0.07216
       0.62140     0.07911
       0.58488     0.08550
       0.54828     0.09116
       0.51175     0.09607
       0.47544     0.10007
       0.43941     0.10309
       0.40389     0.10515
       0.36897     0.10618
       0.33473     0.10623
       0.30138     0.10533
       0.26907     0.10349
       0.23795     0.10079
       0.20820     0.09726
       0.17997     0.09295
       0.15344     0.08790
       0.12873     0.08214
       0.10594     0.07574
       0.08522     0.06875
       0.06662     0.06121
       0.05020     0.05327
       0.03605     0.04497
       0.02418     0.03644
       0.01470     0.02787
       0.00761     0.01929
       0.00277     0.01090
       0.00023     0.00310
       0.00026    -0.00341
       0.00381    -0.00893
       0.01113    -0.01425
       0.02158    -0.01941
       0.03494    -0.02434
       0.05116    -0.02893
       0.07018    -0.03319
       0.09182    -0.03711
       0.11596    -0.04064
       0.14245    -0.04381
       0.17109    -0.04659
       0.20169    -0.04897
       0.23403    -0.05091
       0.26794    -0.05237
       0.30320    -0.05334
       0.33959    -0.05378
       0.37693    -0.05366
       0.41501    -0.05301
       0.45362    -0.05177
       0.49262    -0.04997
       0.53173    -0.04765
       0.57084    -0.04480
       0.60985    -0.04155
       0.64846    -0.03809
       0.68640    -0.03450
       0.72339    -0.03089
       0.75914    -0.02733
       0.79336    -0.02390
       0.82577    -0.02064
       0.85609    -0.01759
       0.88405    -0.01478
       0.90939    -0.01222
       0.93188    -0.00987
       0.95129    -0.00769
       0.96747    -0.00552
       0.98059    -0.00327
       0.99076    -0.00134
       0.99755    -0.00023
       1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GEMINI (smoothed)PreviewDetails
S8036 (16%)PreviewDetails
NASA/LANGLEY NLF(1)-0416 AIRFOILPreviewDetails
NACA 2415PreviewDetails
FX 61-163 AIRFOILPreviewDetails
NACA 2415PreviewDetails
MB253515 15.0% smoothedPreviewDetails
GOE 601 AIRFOILPreviewDetails
GOE 738 AIRFOILPreviewDetails
EPPLER 715 AIRFOILPreviewDetails

Polars for S8037 (16%) (s8037-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s8037-il50,00097.2 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s8037-il50,000522.8 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s8037-il100,000947 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s8037-il100,000548.3 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s8037-il200,000971.3 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s8037-il200,000569 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s8037-il500,000999.9 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s8037-il500,000585.3 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s8037-il1,000,0009110.5 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s8037-il1,000,000598.5 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit