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

GOE 795 AIRFOIL (goe795-il)

GOE 795 AIRFOIL - Gottingen 795 airfoil


Airfoil goe795-il
Details Dat file Parser  
(goe795-il) GOE 795 AIRFOIL
Gottingen 795 airfoil
Max thickness 8% at 30.9% chord.
Max camber 2.4% at 43.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
GOE 795 AIRFOIL
       49.       49.

 0.0000000 0.0000000
 0.0010700 0.0032000
 0.0042800 0.0072000
 0.0096100 0.0119000
 0.0170400 0.0169000
 0.0265300 0.0216000
 0.0380600 0.0258300
 0.0515600 0.0306200
 0.0669900 0.0351600
 0.0842700 0.0393900
 0.1033200 0.0433700
 0.1240800 0.0470100
 0.1464500 0.0503600
 0.1703300 0.0535600
 0.1956200 0.0564800
 0.2222100 0.0588700
 0.2500000 0.0606800
 0.2788600 0.0619300
 0.3086600 0.0628700
 0.3392800 0.0635200
 0.3705900 0.0638500
 0.4024500 0.0638100
 0.4347400 0.0633400
 0.4673000 0.0624200
 0.5000000 0.0610200
 0.5327000 0.0591700
 0.5652600 0.0568800
 0.5975500 0.0542400
 0.6294100 0.0512900
 0.6607200 0.0481300
 0.6913400 0.0448600
 0.7211400 0.0415700
 0.7500000 0.0382600
 0.7777900 0.0349200
 0.8043801 0.0315400
 0.8296700 0.0281400
 0.8535500 0.0247600
 0.8759201 0.0214700
 0.8966800 0.0183200
 0.9157300 0.0153400
 0.9330100 0.0126100
 0.9484400 0.0101500
 0.9619400 0.0078700
 0.9734700 0.0057100
 0.9829600 0.0037900
 0.9903900 0.0021900
 0.9957200 0.0009900
 0.9989300 0.0002500
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0010700 -.0030000
 0.0042800 -.0067000
 0.0096100 -.0095000
 0.0170400 -.0123900
 0.0265300 -.0146700
 0.0380600 -.0164800
 0.0515600 -.0182200
 0.0669900 -.0195000
 0.0842700 -.0201000
 0.1033200 -.0203200
 0.1240800 -.0205400
 0.1464500 -.0206500
 0.1703300 -.0203400
 0.1956200 -.0197000
 0.2222100 -.0190400
 0.2500000 -.0183500
 0.2788600 -.0177900
 0.3086600 -.0171900
 0.3392800 -.0165300
 0.3705900 -.0158300
 0.4024500 -.0151200
 0.4347400 -.0144000
 0.4673000 -.0136900
 0.5000000 -.0129800
 0.5327000 -.0122600
 0.5652600 -.0115400
 0.5975500 -.0108400
 0.6294100 -.0101300
 0.6607200 -.0094500
 0.6913400 -.0087800
 0.7211400 -.0081200
 0.7500000 -.0074900
 0.7777900 -.0068800
 0.8043801 -.0062900
 0.8296700 -.0057400
 0.8535500 -.0052100
 0.8759201 -.0047200
 0.8966800 -.0042700
 0.9157300 -.0038500
 0.9330100 -.0034700
 0.9484400 -.0031300
 0.9619400 -.0027000
 0.9734700 -.0021100
 0.9829600 -.0014800
 0.9903900 -.0008900
 0.9957200 -.0004100
 0.9989300 -.0001100
 1.0000000 0.0000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

GOE 795 smoothedPreviewDetails
GOE 622 AIRFOILPreviewDetails
GOE 564 AIRFOILPreviewDetails
NACA 2408PreviewDetails
N-9PreviewDetails
GOE 515 AIRFOILPreviewDetails
MH 32 8.7%PreviewDetails
MH 30 7.84%PreviewDetails
AG36PreviewDetails
GOE 566 AIRFOILPreviewDetails

Polars for GOE 795 AIRFOIL (goe795-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   goe795-il50,000938 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe795-il50,000537.8 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   goe795-il100,000956.5 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe795-il100,000553.6 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   goe795-il200,000975.4 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   goe795-il200,000567.5 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   goe795-il500,000995.7 at α=3°Mach=0 Ncrit=9Xfoil predictionDetails
   goe795-il500,000580.2 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   goe795-il1,000,0009105 at α=1.75°Mach=0 Ncrit=9Xfoil predictionDetails
   goe795-il1,000,000584.9 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit