KC-135 BL351.6 AIRFOIL (kc135d-il)
KC-135 BL351.6 AIRFOIL - Boeing KC-135 transonic airfoils
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(kc135d-il) KC-135 BL351.6 AIRFOIL Boeing KC-135 transonic airfoils Max thickness 9% at 40% chord. Max camber 1.9% at 30% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
KC-135 BL351.6 AIRFOIL
26.0 26.0
0.0000000 0.0030600
0.0050000 0.0099700
0.0075000 0.0119800
0.0125000 0.0151900
0.0250000 0.0216000
0.0500000 0.0313000
0.0750000 0.0385700
0.1000000 0.0442300
0.1500000 0.0521000
0.2000000 0.0570400
0.2500000 0.0605000
0.3000000 0.0628000
0.3500000 0.0643000
0.4000000 0.0644900
0.4500000 0.0637000
0.5000000 0.0617800
0.5500000 0.0585000
0.6000000 0.0541200
0.6500000 0.0488000
0.7000000 0.0426700
0.7500000 0.0360500
0.8000000 0.0290400
0.8500000 0.0217800
0.9000000 0.0145200
0.9500000 0.0072600
1.0000000 0.0000000
0.0000000 0.0000000
0.0050000 -.0046500
0.0075000 -.0055800
0.0125000 -.0065700
0.0250000 -.0075000
0.0500000 -.0089500
0.0750000 -.0104100
0.1000000 -.0118700
0.1500000 -.0147900
0.2000000 -.0177000
0.2500000 -.0205900
0.3000000 -.0227500
0.3500000 -.0244500
0.4000000 -.0254300
0.4500000 -.0256800
0.5000000 -.0250100
0.5500000 -.0233000
0.6000000 -.0207800
0.6500000 -.0181800
0.7000000 -.0155800
0.7500000 -.0129900
0.8000000 -.0103900
0.8500000 -.0077500
0.9000000 -.0052000
0.9500000 -.0026000
1.0000000 0.0000000
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Polars for KC-135 BL351.6 AIRFOIL (kc135d-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| kc135d-il | 50,000 | 9 | 36.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 50,000 | 5 | 36.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 100,000 | 9 | 54.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 100,000 | 5 | 52.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 200,000 | 9 | 74.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 200,000 | 5 | 68.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 500,000 | 9 | 100.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 500,000 | 5 | 84 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 1,000,000 | 9 | 114.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 1,000,000 | 5 | 86.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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