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NACA 25112 (naca25112-jf)

NACA 25112 - NACA 25112 5 digit reflex airfoil


Airfoil naca25112-jf
Details Dat file Parser  
(naca25112-jf) NACA 25112
NACA 25112 5 digit reflex airfoil
Max thickness 12% at 29.5% chord.
Max camber 2% at 27.2% chord
Source Javafoil generated
Source dat file
The dat file is in Selig format
NACA 25112
0.99998910	0.00125995
0.99930326	0.00135018
0.99724778	0.00162080
0.99382887	0.00207156
0.98905678	0.00270208
0.98294579	0.00351178
0.97551412	0.00449986
0.96678377	0.00566530
0.95678046	0.00700680
0.94553345	0.00852271
0.93307538	0.01021099
0.91944213	0.01206912
0.90467264	0.01409400
0.88880874	0.01628186
0.87189499	0.01862815
0.85397851	0.02112738
0.83510878	0.02377304
0.81533754	0.02655743
0.79471859	0.02947152
0.77330766	0.03250484
0.75116223	0.03564536
0.72834145	0.03887939
0.70490595	0.04219149
0.68091774	0.04556448
0.65644007	0.04897934
0.63153732	0.05241534
0.60627487	0.05585006
0.58071903	0.05925955
0.55493688	0.06261851
0.52899619	0.06590052
0.50296532	0.06907829
0.47691311	0.07212407
0.45090876	0.07500994
0.42499472	0.07770679
0.39916635	0.08016081
0.37348845	0.08230129
0.34803325	0.08406170
0.32287644	0.08538169
0.29809696	0.08620863
0.27377671	0.08649907
0.25000000	0.08621990
0.22685286	0.08534941
0.20442216	0.08387798
0.18279457	0.08180842
0.16205540	0.07915600
0.14228736	0.07594802
0.12356937	0.07222304
0.10597530	0.06802970
0.08957302	0.06342521
0.07442341	0.05847353
0.06057978	0.05324341
0.04808739	0.04780621
0.03698327	0.04223375
0.02729620	0.03659618
0.01904695	0.03095991
0.01224859	0.02538575
0.00690697	0.01992730
0.00302119	0.01462953
0.00058415	0.00952771
-0.00041692	0.00464660
0.00000000	0.00000000
0.00178739	-0.00430862
0.00489395	-0.00818444
0.00929047	-0.01163946
0.01494543	-0.01469111
0.02182558	-0.01736166
0.02989654	-0.01967744
0.03912337	-0.02166809
0.04947127	-0.02336572
0.06090608	-0.02480405
0.07339482	-0.02601768
0.08690603	-0.02704127
0.10140999	-0.02790881
0.11687873	-0.02865302
0.13328581	-0.02930468
0.15060586	-0.02989205
0.16881400	-0.03044028
0.18788504	-0.03097086
0.20779259	-0.03150106
0.22850810	-0.03204336
0.25000000	-0.03260495
0.27223279	-0.03318723
0.29516640	-0.03378549
0.31875562	-0.03438866
0.34294976	-0.03497924
0.36769251	-0.03553345
0.39292196	-0.03602161
0.41857082	-0.03640876
0.44456277	-0.03665542
0.47075094	-0.03673113
0.49703468	-0.03663598
0.52333977	-0.03637474
0.54959159	-0.03595239
0.57571543	-0.03537425
0.60163682	-0.03464597
0.62728173	-0.03377371
0.65257692	-0.03276424
0.67745021	-0.03162506
0.70183069	-0.03036453
0.72564905	-0.02899202
0.74883777	-0.02751801
0.77133138	-0.02595418
0.79306666	-0.02431345
0.81398285	-0.02261004
0.83402183	-0.02085939
0.85312827	-0.01907817
0.87124983	-0.01728411
0.88833722	-0.01549584
0.90434436	-0.01373271
0.91922844	-0.01201453
0.93295002	-0.01036128
0.94547307	-0.00879280
0.95676500	-0.00732844
0.96679666	-0.00598674
0.97554240	-0.00478506
0.98298003	-0.00373925
0.98909082	-0.00286334
0.99385947	-0.00216922
0.99727411	-0.00166643
0.99932628	-0.00136193
1.00001090	-0.00125995
Dat file parser warnings
  • Line 61 - X value too small but included: -0.00041692 0.00464660
  • Line 122 - X value too large but included: 1.00001090 -0.00125995
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Polars for NACA 25112 (naca25112-jf)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca25112-jf50,000917.7 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca25112-jf50,000528.6 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca25112-jf100,000942.5 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   naca25112-jf100,000546.7 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca25112-jf200,000962.9 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca25112-jf200,000563.9 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   naca25112-jf500,000989.9 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca25112-jf500,000585.9 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca25112-jf1,000,0009109.4 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca25112-jf1,000,000598.1 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
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