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

D.G.A. 1182 (dga1182-il)

D.G.A. 1182 - D.G.A. 1182 airfoil


Airfoil dga1182-il
Details Dat file Parser  
(dga1182-il) D.G.A. 1182
D.G.A. 1182 airfoil
Max thickness 7.6% at 30% chord.
Max camber 0.9% at 20% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
D.G.A. 1182
1.0000     0.0030
0.9500     0.0075
0.9000     0.0125
0.8000     0.0210
0.7000     0.0290
0.6000     0.0350
0.5000     0.0400
0.4000     0.0430
0.3000     0.0430
0.2000     0.0400
0.1500     0.0265
0.1000     0.0310
0.0750     0.0280
0.0500     0.0250
0.0250     0.0190
0.0125     0.0140
0.0000     0.0000
0.0125     -0.0055
0.0250     -0.0080
0.0500     -0.0120
0.0750     -0.0150
0.1000     -0.0170
0.1500     -0.0195
0.2000     -0.0210
0.3000     -0.0330
0.4000     -0.0240
0.5000     -0.0230
0.6000     -0.0200
0.7000     -0.0175
0.8000     -0.0125
0.9000     -0.0050
0.9500     -0.0030
1.0000     0.0000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

NASA/AMES 63A108 MOD C AIRFOILPreviewDetails
NASA/AMES A-02 AIRFOILPreviewDetails
Eh 1.0/7.0PreviewDetails
BOEING-VERTOL VR-15 AIRFOILPreviewDetails
M6 (65%)PreviewDetails
BOEING-VERTOL VR-14 AIRFOILPreviewDetails
TSAGI 8% AIRFOILPreviewDetails
S8025 (8%)PreviewDetails
SIKORSKY SSC-A07 AIRFOILPreviewDetails
USA 49 AIRFOILPreviewDetails

Polars for D.G.A. 1182 (dga1182-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   dga1182-il50,000922.6 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   dga1182-il50,000520.6 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   dga1182-il100,000924.2 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   dga1182-il100,000527.8 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   dga1182-il200,000929.3 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   dga1182-il200,000537.5 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   dga1182-il500,000941.5 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   dga1182-il500,000547.6 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   dga1182-il1,000,000957.6 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   dga1182-il1,000,000555.7 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit