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

SD7090 (10%) (sd7090-il)

SD7090 (10%) - Selig/Donovan SD7090 low Reynolds number airfoil


Airfoil sd7090-il
Details Dat file Parser  
(sd7090-il) SD7090 (10%)
Selig/Donovan SD7090 low Reynolds number airfoil
Max thickness 10% at 29.3% chord.
Max camber 1.5% at 43.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
  SD7090 (10%)
  1.00000  0.0
  0.99655  0.00050
  0.98664  0.00219
  0.97113  0.00512
  0.95062  0.00882
  0.92522  0.01284
  0.89500  0.01718
  0.86036  0.02188
  0.82176  0.02691
  0.77972  0.03218
  0.73479  0.03760
  0.68754  0.04304
  0.63860  0.04834
  0.58850  0.05329
  0.53777  0.05773
  0.48692  0.06153
  0.43649  0.06457
  0.38699  0.06674
  0.33890  0.06795
  0.29269  0.06814
  0.24878  0.06724
  0.20759  0.06522
  0.16945  0.06206
  0.13467  0.05780
  0.10352  0.05249
  0.07624  0.04621
  0.05297  0.03907
  0.03384  0.03125
  0.01891  0.02298
  0.00827  0.01458
  0.00196  0.00637
  0.00005 -0.00097
  0.00345 -0.00734
  0.01238 -0.01318
  0.02624 -0.01834
  0.04514 -0.02262
  0.06903 -0.02605
  0.09771 -0.02873
  0.13087 -0.03067
  0.16817 -0.03188
  0.20926 -0.03240
  0.25371 -0.03229
  0.30106 -0.03161
  0.35077 -0.03046
  0.40227 -0.02889
  0.45499 -0.02696
  0.50832 -0.02472
  0.56166 -0.02221
  0.61442 -0.01948
  0.66605 -0.01658
  0.71605 -0.01363
  0.76381 -0.01083
  0.80869 -0.00829
  0.85007 -0.00609
  0.88735 -0.00426
  0.92001 -0.00279
  0.94757 -0.00160
  0.96974 -0.00066
  0.98622 -0.00009
  0.99650  0.00004
  1.00001  0.00000
Dat file parser warnings
  • Line 62 - X value too large but included: 1.00001 0.00000
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

RAF 28 AIRFOILPreviewDetails
S3016-095-87PreviewDetails
SD8040 (10%)PreviewDetails
NACA 2410PreviewDetails
MH 61 10.26%PreviewDetails
HUGHES HELICOPTERS HH-02 AIRFOILPreviewDetails
RG 14 10% AIRFOILPreviewDetails
MH 60 10.08%PreviewDetails
NACA 1410PreviewDetails
MH 45 9.85%PreviewDetails

Polars for SD7090 (10%) (sd7090-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   sd7090-il50,000930.7 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   sd7090-il50,000534.2 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   sd7090-il100,000947.1 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sd7090-il100,000547.6 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   sd7090-il200,000962.9 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sd7090-il200,000560.6 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   sd7090-il500,000983.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sd7090-il500,000578.3 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   sd7090-il1,000,000999 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   sd7090-il1,000,000592.2 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit