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

Joukovsky f=0% t=15% (joukowsk0015-jf)

Joukovsky f=0% t=15% - Joukowski 15% symmetrical airfoil


Airfoil joukowsk0015-jf
Details Dat file Parser  
(joukowsk0015-jf) Joukovsky f=0% t=15%
Joukowski 15% symmetrical airfoil
Max thickness 15% at 24.6% chord.
Max camber 0% at 0% chord
Source Javafoil generated
Source dat file
The dat file is in Selig format
Joukovsky f=0% t=15%
1.00000000	0.00000000
0.99553626	0.00006943
0.98889372	0.00027162
0.98010329	0.00064856
0.96920563	0.00124213
0.95625086	0.00208987
0.94129813	0.00322376
0.92441513	0.00466929
0.90567763	0.00644498
0.88516885	0.00856160
0.86297898	0.01102210
0.83920456	0.01382104
0.81394795	0.01694482
0.78731676	0.02037157
0.75942338	0.02407136
0.73038445	0.02800672
0.70032045	0.03213295
0.66935529	0.03639886
0.63761600	0.04074746
0.60523235	0.04511683
0.57233661	0.04944101
0.53906334	0.05365110
0.50554911	0.05767623
0.47193236	0.06144472
0.43835315	0.06488519
0.40495303	0.06792774
0.37187479	0.07050506
0.33926229	0.07255356
0.30726022	0.07401437
0.27601389	0.07483438
0.24566898	0.07496701
0.21637140	0.07437301
0.18826716	0.07302137
0.16150235	0.07088958
0.13622350	0.06796367
0.11257818	0.06423948
0.09071652	0.05972180
0.07079358	0.05442629
0.05297393	0.04838031
0.03743803	0.04163000
0.02439101	0.03425469
0.01406518	0.02640602
0.00668080	0.01839319
0.00227441	0.01079997
0.00038317	0.00444327
0.00000000	-0.00000000
0.00038317	-0.00444327
0.00227441	-0.01079997
0.00668080	-0.01839319
0.01406518	-0.02640602
0.02439101	-0.03425469
0.03743803	-0.04163000
0.05297393	-0.04838031
0.07079358	-0.05442629
0.09071652	-0.05972180
0.11257818	-0.06423948
0.13622350	-0.06796367
0.16150235	-0.07088958
0.18826716	-0.07302137
0.21637140	-0.07437301
0.24566898	-0.07496701
0.27601389	-0.07483438
0.30726022	-0.07401437
0.33926229	-0.07255356
0.37187479	-0.07050506
0.40495303	-0.06792774
0.43835315	-0.06488519
0.47193236	-0.06144472
0.50554911	-0.05767623
0.53906334	-0.05365110
0.57233661	-0.04944101
0.60523235	-0.04511683
0.63761600	-0.04074746
0.66935529	-0.03639886
0.70032045	-0.03213295
0.73038445	-0.02800672
0.75942338	-0.02407136
0.78731676	-0.02037157
0.81394795	-0.01694482
0.83920456	-0.01382104
0.86297898	-0.01102210
0.88516885	-0.00856160
0.90567763	-0.00644498
0.92441513	-0.00466929
0.94129813	-0.00322376
0.95625086	-0.00208987
0.96920563	-0.00124213
0.98010329	-0.00064856
0.98889372	-0.00027162
0.99553626	-0.00006943
1.00000000	0.00000000
No parser warnings Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

E475 (15.01%)PreviewDetails
E169 (14.4%)PreviewDetails
NACA 0015PreviewDetails
BOEING 737 ROOT AIRFOILPreviewDetails
E474 (14.09%)PreviewDetails
S1048 14% (Danny Howell)PreviewDetails
S8035 for RC aerobatic 14% thickPreviewDetails
FX LIII-142 K 25 AIRFOILPreviewDetails
EPPLER 473 AIRFOILPreviewDetails
OAF139 AIRFOILPreviewDetails

Polars for Joukovsky f=0% t=15% (joukowsk0015-jf)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   joukowsk0015-jf50,000917.8 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   joukowsk0015-jf50,000525.6 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   joukowsk0015-jf100,000935 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   joukowsk0015-jf100,000538 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   joukowsk0015-jf200,000949.7 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   joukowsk0015-jf200,000550.8 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   joukowsk0015-jf500,000970.3 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   joukowsk0015-jf500,000568.4 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   joukowsk0015-jf1,000,000985.8 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   joukowsk0015-jf1,000,000582 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit