KC-135 BL124.32 AIRFOIL (kc135b-il)
KC-135 BL124.32 AIRFOIL - Boeing KC-135 transonic airfoils
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(kc135b-il) KC-135 BL124.32 AIRFOIL Boeing KC-135 transonic airfoils Max thickness 13% at 40% chord. Max camber 1.4% at 20% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
KC-135 BL124.32 AIRFOIL
26.0 26.0
0.0000000 0.0053600
0.0050000 0.0139900
0.0075000 0.0165400
0.0125000 0.0206000
0.0250000 0.0284000
0.0500000 0.0399800
0.0750000 0.0485000
0.1000000 0.0551100
0.1500000 0.0643600
0.2000000 0.0707000
0.2500000 0.0750000
0.3000000 0.0776000
0.3500000 0.0792000
0.4000000 0.0791000
0.4500000 0.0772500
0.5000000 0.0738200
0.5500000 0.0689500
0.6000000 0.0628400
0.6500000 0.0557000
0.7000000 0.0478200
0.7500000 0.0398500
0.8000000 0.0318800
0.8500000 0.0239100
0.9000000 0.0159400
0.9500000 0.0079700
1.0000000 0.0000000
0.0000000 0.0000000
0.0050000 -.0073300
0.0075000 -.0089500
0.0125000 -.0112300
0.0250000 -.0147500
0.0500000 -.0191500
0.0750000 -.0229000
0.1000000 -.0264600
0.1500000 -.0331800
0.2000000 -.0392500
0.2500000 -.0440100
0.3000000 -.0474600
0.3500000 -.0498000
0.4000000 -.0507000
0.4500000 -.0500700
0.5000000 -.0479300
0.5500000 -.0444800
0.6000000 -.0399500
0.6500000 -.0349600
0.7000000 -.0299600
0.7500000 -.0249700
0.8000000 -.0199800
0.8500000 -.0149800
0.9000000 -.0099900
0.9500000 -.0049900
1.0000000 0.0000000
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Polars for KC-135 BL124.32 AIRFOIL (kc135b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| kc135b-il | 50,000 | 9 | 31.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 50,000 | 5 | 31.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135b-il | 100,000 | 9 | 50.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 100,000 | 5 | 49.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135b-il | 200,000 | 9 | 70.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 200,000 | 5 | 62.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135b-il | 500,000 | 9 | 89.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 500,000 | 5 | 71.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135b-il | 1,000,000 | 9 | 98.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 1,000,000 | 5 | 79.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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