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

S7012 8.75% (s7012-il)

S7012 8.75% - Selig S7012 low Reynolds number airfoil


Airfoil s7012-il
Details Dat file Parser  
(s7012-il) S7012 8.75%
Selig S7012 low Reynolds number airfoil
Max thickness 8.7% at 27.7% chord.
Max camber 1.7% at 38.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S7012 8.75%
       1.00000     0.00000
       0.99819     0.00024
       0.99294     0.00104
       0.98451     0.00231
       0.97296     0.00392
       0.95833     0.00586
       0.94077     0.00817
       0.92044     0.01080
       0.89749     0.01372
       0.87210     0.01689
       0.84445     0.02029
       0.81474     0.02386
       0.78318     0.02757
       0.74999     0.03138
       0.71540     0.03524
       0.67965     0.03909
       0.64298     0.04287
       0.60563     0.04654
       0.56785     0.05002
       0.52988     0.05324
       0.49193     0.05615
       0.45426     0.05870
       0.41710     0.06081
       0.38070     0.06241
       0.34520     0.06335
       0.31071     0.06360
       0.27741     0.06319
       0.24543     0.06209
       0.21486     0.06033
       0.18590     0.05795
       0.15865     0.05496
       0.13326     0.05143
       0.10983     0.04738
       0.08846     0.04287
       0.06926     0.03798
       0.05229     0.03274
       0.03759     0.02728
       0.02525     0.02167
       0.01528     0.01605
       0.00773     0.01058
       0.00266     0.00542
       0.00007     0.00087
       0.00069    -0.00278
       0.00486    -0.00600
       0.01208    -0.00918
       0.02223    -0.01220
       0.03523    -0.01495
       0.05102    -0.01739
       0.06952    -0.01950
       0.09065    -0.02126
       0.11428    -0.02265
       0.14032    -0.02368
       0.16861    -0.02436
       0.19900    -0.02471
       0.23131    -0.02474
       0.26535    -0.02448
       0.30091    -0.02396
       0.33778    -0.02318
       0.37572    -0.02220
       0.41449    -0.02101
       0.45383    -0.01965
       0.49348    -0.01813
       0.53316    -0.01644
       0.57261    -0.01453
       0.61171    -0.01227
       0.65044    -0.00978
       0.68859    -0.00732
       0.72582    -0.00504
       0.76182    -0.00300
       0.79628    -0.00128
       0.82889     0.00010
       0.85936     0.00112
       0.88743     0.00178
       0.91283     0.00211
       0.93533     0.00214
       0.95473     0.00192
       0.97084     0.00153
       0.98352     0.00105
       0.99266     0.00055
       0.99816     0.00016
       1.00000     0.00000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

RG 14 AIRFOILPreviewDetails
RG-15 8.9%PreviewDetails
MH 64 8.59%PreviewDetails
MH 46 9.1%PreviewDetails
MH 42 8.94%PreviewDetails
MH 43 8.5%PreviewDetails
RG 14 9% AIRFOILPreviewDetails
AG35PreviewDetails
MH 62 9.3%PreviewDetails
SD7003-085-88PreviewDetails

Polars for S7012 8.75% (s7012-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s7012-il50,000933.7 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
   s7012-il50,000537.5 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s7012-il100,000951.9 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s7012-il100,000552.8 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s7012-il200,000970.3 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s7012-il200,000567.5 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s7012-il500,000994.1 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   s7012-il500,000585.7 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s7012-il1,000,0009110.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s7012-il1,000,000597 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit