BOEING 707 .08 SPAN AIRFOIL (b707a-il)
BOEING 707 .08 SPAN AIRFOIL - Boeing Commercial Airplane Company model 707 airfoils
| Details | Dat file | Parser | |
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(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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Polars for BOEING 707 .08 SPAN AIRFOIL (b707a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| b707a-il | 50,000 | 9 | 16.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707a-il | 50,000 | 5 | 20.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707a-il | 100,000 | 9 | 26.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707a-il | 100,000 | 5 | 32.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707a-il | 200,000 | 9 | 43.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707a-il | 200,000 | 5 | 43.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707a-il | 500,000 | 9 | 59.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707a-il | 500,000 | 5 | 52.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707a-il | 1,000,000 | 9 | 64.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707a-il | 1,000,000 | 5 | 59.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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