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NACA 22112 (naca22112-jf)

NACA 22112 - NACA 22112 5 digit reflex airfoil


Airfoil naca22112-jf
Details Dat file Parser  
(naca22112-jf) NACA 22112
NACA 22112 5 digit reflex airfoil
Max thickness 12% at 29.5% chord.
Max camber 0.8% at 9.6% chord
Source Javafoil generated
Source dat file
The dat file is in Selig format
NACA 22112
1.00000901	0.00125997
0.99932450	0.00136098
0.99727288	0.00166336
0.99385985	0.00216516
0.98909489	0.00286317
0.98299124	0.00375296
0.97556586	0.00482900
0.96683933	0.00608471
0.95683585	0.00751258
0.94558311	0.00910428
0.93311226	0.01085075
0.91945775	0.01274233
0.90465727	0.01476886
0.88875164	0.01691973
0.87178465	0.01918396
0.85380298	0.02155026
0.83485603	0.02400702
0.81499582	0.02654235
0.79427678	0.02914403
0.77275567	0.03179951
0.75049136	0.03449582
0.72754472	0.03721954
0.70397840	0.03995677
0.67985671	0.04269299
0.65524542	0.04541310
0.63021158	0.04810133
0.60482334	0.05074126
0.57914980	0.05331583
0.55326077	0.05580738
0.52722666	0.05819775
0.50111822	0.06046837
0.47500642	0.06260044
0.44896223	0.06457512
0.42305645	0.06637373
0.39735952	0.06797801
0.37194134	0.06937038
0.34687113	0.07053422
0.32221717	0.07145413
0.29804669	0.07211624
0.27442566	0.07250844
0.25141864	0.07262061
0.22908856	0.07244481
0.20749660	0.07197545
0.18670197	0.07120936
0.16676180	0.07014586
0.14773090	0.06878670
0.12965588	0.06713609
0.11214374	0.06514893
0.09513781	0.06262772
0.07892074	0.05941319
0.06375795	0.05543591
0.04988757	0.05071555
0.03750838	0.04535018
0.02676964	0.03949715
0.01776637	0.03334885
0.01054133	0.02710779
0.00509256	0.02096472
0.00138344	0.01508213
-0.00064742	0.00958326
-0.00107846	0.00454588
0.00000000	0.00000000
0.00244893	-0.00397540
0.00612553	-0.00734074
0.01092822	-0.01018170
0.01675984	-0.01260500
0.02353284	-0.01472856
0.03117711	-0.01667121
0.03964993	-0.01854341
0.04894617	-0.02044053
0.05910591	-0.02243902
0.07021664	-0.02459428
0.08240869	-0.02693744
0.09584519	-0.02946743
0.11071030	-0.03213611
0.12719929	-0.03482593
0.14516232	-0.03734868
0.16410760	-0.03962653
0.18397764	-0.04165187
0.20471815	-0.04341937
0.22627241	-0.04492585
0.24858136	-0.04617036
0.27158384	-0.04715407
0.29521667	-0.04788030
0.31941488	-0.04835432
0.34411188	-0.04858326
0.36923961	-0.04857587
0.39472879	-0.04834235
0.42050909	-0.04789409
0.44650930	-0.04724350
0.47265762	-0.04640374
0.49888178	-0.04538851
0.52510930	-0.04421192
0.55126769	-0.04288823
0.57728467	-0.04143180
0.60308835	-0.03985693
0.62860747	-0.03817781
0.65377157	-0.03640844
0.67851124	-0.03456267
0.70275824	-0.03265414
0.72644578	-0.03069635
0.74950864	-0.02870267
0.77188337	-0.02668640
0.79350847	-0.02466081
0.81432457	-0.02263919
0.83427457	-0.02063486
0.85330380	-0.01866119
0.87136018	-0.01673158
0.88839432	-0.01485946
0.90435972	-0.01305819
0.91921282	-0.01134102
0.93291314	-0.00972094
0.94542341	-0.00821060
0.95670961	-0.00682210
0.96674110	-0.00556691
0.97549066	-0.00445565
0.98293458	-0.00349792
0.98905271	-0.00270220
0.99382849	-0.00207562
0.99724901	-0.00162388
0.99930503	-0.00135116
0.99999099	-0.00125997

Dat file parser warnings
  • Line 2 - X value too large but included: 1.00000901 0.00125997
  • Line 60 - X value too small but included: -0.00064742 0.00958326
  • Line 61 - X value too small but included: -0.00107846 0.00454588
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Polars for NACA 22112 (naca22112-jf)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca22112-jf50,000923.9 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca22112-jf50,000526.4 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca22112-jf100,000933.9 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca22112-jf100,000536.8 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca22112-jf200,000945.7 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca22112-jf200,000549.5 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   naca22112-jf500,000967.7 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca22112-jf500,000571.6 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca22112-jf1,000,000989.4 at α=9.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca22112-jf1,000,000589.4 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
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