DAVIS BASIC B-24 WING AIRFOIL (davis-corrected-il)
DAVIS BASIC B-24 WING AIRFOIL - Davis basic B-24 wing airfoil
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(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)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| davis-corrected-il | 50,000 | 9 | 12.5 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 100,000 | 9 | 36.4 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 200,000 | 9 | 63.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 500,000 | 9 | 96.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 1,000,000 | 9 | 122.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 2,000,000 | 9 | 137.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 5,000,000 | 9 | 157.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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