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BOEING 707 .08 SPAN AIRFOIL (b707a-il)

BOEING 707 .08 SPAN AIRFOIL - Boeing Commercial Airplane Company model 707 airfoils


Airfoil b707a-il
Details Dat file Parser  
(b707a-il) BOEING 707 .08 SPAN AIRFOIL
Boeing Commercial Airplane Company model 707 airfoils
Max thickness 11.4% at 24% chord.
Max camber 0.2% at 6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Lednicer format
BOEING 707 .08 SPAN AIRFOIL
      61.       61.

 0.0000000 0.0000000
 0.0005000 0.0064638
 0.0010000 0.0084488
 0.0020000 0.0110085
 0.0040000 0.0140317
 0.0080000 0.0175265
 0.0120000 0.0209530
 0.0200000 0.0272234
 0.0300000 0.0326742
 0.0400000 0.0360978
 0.0500000 0.0387719
 0.0600000 0.0413505
 0.0800000 0.0454360
 0.1000000 0.0476525
 0.1200000 0.0491397
 0.1400000 0.0500832
 0.1600000 0.0504598
 0.1800000 0.0504723
 0.2000000 0.0505076
 0.2200000 0.0506790
 0.2400000 0.0502123
 0.2600000 0.0482429
 0.2800000 0.0456843
 0.3000000 0.0439763
 0.3200000 0.0430062
 0.3400000 0.0425267
 0.3600000 0.0422943
 0.3800000 0.0420659
 0.4000000 0.0416033
 0.4200000 0.0407363
 0.4400000 0.0395394
 0.4600000 0.0381409
 0.4800000 0.0366673
 0.5000000 0.0352476
 0.5200000 0.0339760
 0.5400000 0.0328278
 0.5600000 0.0317559
 0.5800000 0.0307107
 0.6000000 0.0296456
 0.6200000 0.0285267
 0.6400000 0.0273739
 0.6600000 0.0262196
 0.6800000 0.0250949
 0.7000000 0.0240321
 0.7200000 0.0230489
 0.7400000 0.0221102
 0.7600000 0.0211718
 0.7800000 0.0201870
 0.8000000 0.0191108
 0.8200000 0.0179036
 0.8400000 0.0165478
 0.8600000 0.0150329
 0.8800000 0.0133449
 0.9000000 0.0114733
 0.9200000 0.0094145
 0.9400000 0.0071976
 0.9600000 0.0048649
 0.9700000 0.0036652
 0.9800000 0.0024506
 0.9900000 0.0012275
 1.0000000 0.0000000

 0.0000000 0.0000000
 0.0005000 -.0046938
 0.0010000 -.0068122
 0.0020000 -.0095513
 0.0040000 -.0128330
 0.0080000 -.0162748
 0.0120000 -.0189872
 0.0200000 -.0241108
 0.0300000 -.0290301
 0.0400000 -.0321990
 0.0500000 -.0345765
 0.0600000 -.0368498
 0.0800000 -.0415383
 0.1000000 -.0461846
 0.1200000 -.0502606
 0.1400000 -.0537201
 0.1600000 -.0566756
 0.1800000 -.0591680
 0.2000000 -.0611521
 0.2200000 -.0626515
 0.2400000 -.0640784
 0.2600000 -.0659499
 0.2800000 -.0679186
 0.3000000 -.0689475
 0.3200000 -.0690421
 0.3400000 -.0683785
 0.3600000 -.0671287
 0.3800000 -.0654627
 0.4000000 -.0635503
 0.4200000 -.0615419
 0.4400000 -.0594897
 0.4600000 -.0574125
 0.4800000 -.0553319
 0.5000000 -.0532648
 0.5200000 -.0512286
 0.5400000 -.0492102
 0.5600000 -.0471911
 0.5800000 -.0451534
 0.6000000 -.0430761
 0.6200000 -.0409454
 0.6400000 -.0387685
 0.6600000 -.0365568
 0.6800000 -.0343263
 0.7000000 -.0320878
 0.7200000 -.0298565
 0.7400000 -.0276400
 0.7600000 -.0254497
 0.7800000 -.0232958
 0.8000000 -.0211866
 0.8200000 -.0191282
 0.8400000 -.0171026
 0.8600000 -.0150853
 0.8800000 -.0130551
 0.9000000 -.0109869
 0.9200000 -.0088630
 0.9400000 -.0066907
 0.9600000 -.0044805
 0.9700000 -.0033653
 0.9800000 -.0022462
 0.9900000 -.0011243
 1.0000000 0.0000000
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Lednicer format dat file
Selig format dat file

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Polars for BOEING 707 .08 SPAN AIRFOIL (b707a-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   b707a-il50,000916.3 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   b707a-il50,000520.7 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   b707a-il100,000926.4 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   b707a-il100,000532.2 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   b707a-il200,000943.1 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   b707a-il200,000543.6 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   b707a-il500,000959.1 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   b707a-il500,000552.4 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   b707a-il1,000,000964.4 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   b707a-il1,000,000559.4 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
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