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

NACA 24112 (naca24112-jf)

NACA 24112 - NACA 24112 5 digit reflex airfoil


Airfoil naca24112-jf
Details Dat file Parser  
(naca24112-jf) NACA 24112
NACA 24112 5 digit reflex airfoil
Max thickness 12% at 29.4% chord.
Max camber 1.7% at 20.6% chord
Source Javafoil generated
Source dat file
The dat file is in Selig format
NACA 24112
0.99999690	0.00126000
0.99931157	0.00135445
0.99725756	0.00163747
0.99384084	0.00210804
0.98907132	0.00276449
0.98296282	0.00360449
0.97553298	0.00462510
0.96680319	0.00582282
0.95679850	0.00719358
0.94554749	0.00873276
0.93308217	0.01043528
0.91943785	0.01229552
0.90465298	0.01430741
0.88876903	0.01646435
0.87183035	0.01875920
0.85388399	0.02118425
0.83497957	0.02373115
0.81516911	0.02639083
0.79450692	0.02915341
0.77304938	0.03200814
0.75085483	0.03494330
0.72798339	0.03794608
0.70449684	0.04100253
0.68045841	0.04409752
0.65593267	0.04721464
0.63098538	0.05033625
0.60568330	0.05344349
0.58009406	0.05651633
0.55428603	0.05953366
0.52832813	0.06247349
0.50228973	0.06531309
0.47624046	0.06802925
0.45025011	0.07059854
0.42438842	0.07299761
0.39872499	0.07520355
0.37332911	0.07719419
0.34826955	0.07894848
0.32361447	0.08044685
0.29933204	0.08166344
0.27537731	0.08251831
0.25183720	0.08292008
0.22880441	0.08279257
0.20637611	0.08207687
0.18465267	0.08073306
0.16373597	0.07874120
0.14372756	0.07610169
0.12472648	0.07283495
0.10682703	0.06898021
0.09011669	0.06459358
0.07467418	0.05974540
0.06056795	0.05451705
0.04785516	0.04899737
0.03658116	0.04327891
0.02677943	0.03745416
0.01847198	0.03161200
0.01167005	0.02583448
0.00637501	0.02019401
0.00257931	0.01475107
0.00026754	0.00955243
-0.00058271	0.00462997
0.00000000	0.00000000
0.00195318	-0.00423705
0.00521056	-0.00799354
0.00973235	-0.01129117
0.01547739	-0.01416000
0.02240412	-0.01663715
0.03047151	-0.01876524
0.03964015	-0.02059073
0.04987338	-0.02216234
0.06113831	-0.02352936
0.07340665	-0.02474022
0.08665525	-0.02584111
0.10086631	-0.02687479
0.11602701	-0.02787946
0.13212870	-0.02888769
0.14916565	-0.02992541
0.16713342	-0.03101071
0.18602694	-0.03215268
0.20583863	-0.03335014
0.22655656	-0.03459036
0.24816280	-0.03584793
0.27063220	-0.03708385
0.29393132	-0.03824491
0.31801758	-0.03926361
0.34271346	-0.04007134
0.36785185	-0.04065579
0.39336331	-0.04102295
0.41917711	-0.04117974
0.44522143	-0.04113389
0.47142358	-0.04089378
0.49771027	-0.04046833
0.52400782	-0.03986691
0.55024243	-0.03909922
0.57634040	-0.03817529
0.60222839	-0.03710542
0.62783366	-0.03590022
0.65308432	-0.03457059
0.67790954	-0.03312781
0.70223981	-0.03158355
0.72600711	-0.02994995
0.74914517	-0.02823970
0.77158965	-0.02646605
0.79327833	-0.02464290
0.81415128	-0.02278477
0.83415104	-0.02090683
0.85322279	-0.01902485
0.87131447	-0.01715514
0.88837693	-0.01531443
0.90436402	-0.01351973
0.91923272	-0.01178820
0.93294323	-0.01013691
0.94545904	-0.00858262
0.95674696	-0.00714157
0.96677723	-0.00582919
0.97552353	-0.00465985
0.98296300	-0.00364662
0.98907628	-0.00280104
0.99384750	-0.00213285
0.99726434	-0.00164985
0.99931797	-0.00135775
1.00000310	-0.00126000
Dat file parser warnings
  • Line 61 - X value too small but included: -0.00058271 0.00462997
  • Line 122 - X value too large but included: 1.00000310 -0.00126000
Send to airfoil plotter
Add to comparison
Lednicer format dat file
Selig format dat file

Similar airfoils

EH 2.0/12PreviewDetails
GOE 766 AIRFOILPreviewDetails
NACA 25112PreviewDetails
NACA 23112PreviewDetails
ONERA NACA CAMBRE AIRFOILPreviewDetails
NACA 23012 12%PreviewDetails
EPPLER 335 AIRFOILPreviewDetails
GOE 676 (= M 12) AIRFOILPreviewDetails
NACA M12 AIRFOILPreviewDetails
NACA M12PreviewDetails

Polars for NACA 24112 (naca24112-jf)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca24112-jf50,000919.9 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca24112-jf50,000527.6 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca24112-jf100,000937.3 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca24112-jf100,000543.5 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   naca24112-jf200,000957.7 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca24112-jf200,000560.4 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca24112-jf500,000984.9 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca24112-jf500,000583 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   naca24112-jf1,000,0009105.5 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca24112-jf1,000,000598.1 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
Reynolds number calculator
Set Reynolds number and Ncrit rangeLowHigh
Reynolds Number
NCrit