KC-135 BL52.44 AIRFOIL (kc135a-il)
KC-135 BL52.44 AIRFOIL - Boeing KC-135 transonic airfoils
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(kc135a-il) KC-135 BL52.44 AIRFOIL Boeing KC-135 transonic airfoils Max thickness 15.5% at 35% chord. Max camber 1.3% at 20% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
KC-135 BL52.44 AIRFOIL
26.0 26.0
0.0000000 0.0074000
0.0050000 0.0175000
0.0075000 0.0205500
0.0125000 0.0253900
0.0250000 0.0347000
0.0500000 0.0483000
0.0750000 0.0581300
0.1000000 0.0657200
0.1500000 0.0766100
0.2000000 0.0838000
0.2500000 0.0886000
0.3000000 0.0913700
0.3500000 0.0921800
0.4000000 0.0910500
0.4500000 0.0876600
0.5000000 0.0825800
0.5500000 0.0762000
0.6000000 0.0687000
0.6500000 0.0602900
0.7000000 0.0516800
0.7500000 0.0430000
0.8000000 0.0344500
0.8500000 0.0258400
0.9000000 0.0172300
0.9500000 0.0086100
1.0000000 0.0000000
0.0000000 0.0000000
0.0050000 -.0087200
0.0075000 -.0107600
0.0125000 -.0139000
0.0250000 -.0191500
0.0500000 -.0261300
0.0750000 -.0317800
0.1000000 -.0366500
0.1500000 -.0451000
0.2000000 -.0522800
0.2500000 -.0575700
0.3000000 -.0610400
0.3500000 -.0627500
0.4000000 -.0625000
0.4500000 -.0604400
0.5000000 -.0567800
0.5500000 -.0518500
0.6000000 -.0461800
0.6500000 -.0404100
0.7000000 -.0346400
0.7500000 -.0288600
0.8000000 -.0230900
0.8500000 -.0173200
0.9000000 -.0115500
0.9500000 -.0057700
1.0000000 0.0000000
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Polars for KC-135 BL52.44 AIRFOIL (kc135a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| kc135a-il | 50,000 | 9 | 24.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 50,000 | 5 | 27.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135a-il | 100,000 | 9 | 47.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 100,000 | 5 | 47.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135a-il | 200,000 | 9 | 68.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 200,000 | 5 | 62.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135a-il | 500,000 | 9 | 88.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 500,000 | 5 | 73.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135a-il | 1,000,000 | 9 | 97.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 1,000,000 | 5 | 82.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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