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DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il)

DAVIS BASIC B-24 WING AIRFOIL - Davis basic B-24 wing airfoil


Airfoil davis-corrected-il
Details Dat file Parser  
(davis-corrected-il) DAVIS BASIC B-24 WING AIRFOIL
Davis basic B-24 wing airfoil
Max thickness 15.9% at 29.6% chord.
Max camber 2.5% at 29.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
DAVIS BASIC B-24 WING AIRFOIL
      62.0      30.0

 0.0000000 0.0000000
 0.0000330 0.0056890
 0.0016440 0.0114680
 0.0047420 0.0173060
 0.0092370 0.0231710
 0.0150360 0.0290350
 0.0220430 0.0348650
 0.0301620 0.0406310
 0.0392970 0.0463040
 0.0493470 0.0518520
 0.0602140 0.0572450
 0.0717970 0.0624530
 0.0839930 0.0674470
 0.0967000 0.0721960
 0.1098160 0.0766720
 0.1232350 0.0808450
 0.1368560 0.0846870
 0.1505920 0.0881760
 0.1644370 0.0913090
 0.1784030 0.0940900
 0.1925020 0.0965240
 0.2067460 0.0986160
 0.2211480 0.1003700
 0.2357180 0.1017940
 0.2504690 0.1028920
 0.2654110 0.1036710
 0.2805560 0.1041390
 0.2959140 0.1043020
 0.3114960 0.1041680
 0.3273120 0.1037450
 0.3433720 0.1030410
 0.3596850 0.1020650
 0.3762620 0.1008270
 0.3931100 0.0993350
 0.4102390 0.0975980
 0.4276570 0.0956280
 0.4453720 0.0934340
 0.4633920 0.0910270
 0.4817230 0.0884180
 0.5003740 0.0856160
 0.5193490 0.0826350
 0.5386560 0.0794840
 0.5583000 0.0761770
 0.5782860 0.0727240
 0.5986190 0.0691380
 0.6193040 0.0654310
 0.6403450 0.0616150
 0.6617440 0.0577030
 0.6835060 0.0537080
 0.7056340 0.0496410
 0.7281280 0.0455160
 0.7509910 0.0413460
 0.7742250 0.0371440
 0.7978300 0.0329220
 0.8218070 0.0286930
 0.8461560 0.0244720
 0.8708760 0.0202690
 0.8959670 0.0160990
 0.9214270 0.0119740
 0.9472540 0.0079080
 0.9734460 0.0039120
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0016320 -.0055700
 0.0050150 -.0109890
 0.0102320 -.0162290
 0.0173650 -.0212590
 0.0264920 -.0260490
 0.0376910 -.0305700
 0.0510340 -.0347930
 0.0665940 -.0386900
 0.0844390 -.0422320
 0.1046350 -.0453910
 0.1272450 -.0481410
 0.1523300 -.0504540
 0.1799450 -.0523040
 0.2101460 -.0536650
 0.2429830 -.0545120
 0.2785030 -.0548210
 0.3167510 -.0545670
 0.3577690 -.0537290
 0.4015930 -.0522820
 0.4482580 -.0502050
 0.4977950 -.0474780
 0.5502310 -.0440810
 0.6055900 -.0399930
 0.6638920 -.0351960
 0.7251530 -.0296740
 0.7893870 -.0234080
 0.8566030 -.0163840
 0.9268070 -.0085860
 1.0000000 0.0000000
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Polars for DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   davis-corrected-il50,000912.5 at α=-0.75°Mach=0 Ncrit=9Xfoil predictionDetails
   davis-corrected-il100,000936.4 at α=11.5°Mach=0 Ncrit=9Xfoil predictionDetails
   davis-corrected-il200,000963.9 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   davis-corrected-il500,000996.3 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   davis-corrected-il1,000,0009122.3 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   davis-corrected-il2,000,0009137.5 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   davis-corrected-il5,000,0009157.6 at α=7°Mach=0 Ncrit=9Xfoil predictionDetails
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