KC-135 BL200.76 AIRFOIL (kc135c-il)
KC-135 BL200.76 AIRFOIL - Boeing KC-135 transonic airfoils
| Details | Dat file | Parser | |
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(kc135c-il) KC-135 BL200.76 AIRFOIL Boeing KC-135 transonic airfoils Max thickness 10.6% at 40% chord. Max camber 1.5% at 25% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
KC-135 BL200.76 AIRFOIL
26.0 26.0
0.0000000 0.0037400
0.0050000 0.0112300
0.0075000 0.0134000
0.0125000 0.0168700
0.0250000 0.0235000
0.0500000 0.0336000
0.0750000 0.0411400
0.1000000 0.0469900
0.1500000 0.0553000
0.2000000 0.0604700
0.2500000 0.0642200
0.3000000 0.0666600
0.3500000 0.0680500
0.4000000 0.0682900
0.4500000 0.0673600
0.5000000 0.0650900
0.5500000 0.0613600
0.6000000 0.0564300
0.6500000 0.0504900
0.7000000 0.0438000
0.7500000 0.0368700
0.8000000 0.0292900
0.8500000 0.0219700
0.9000000 0.0146500
0.9500000 0.0073200
1.0000000 0.0000000
0.0000000 0.0000000
0.0050000 -.0057000
0.0075000 -.0068400
0.0125000 -.0083700
0.0250000 -.0105300
0.0500000 -.0130700
0.0750000 -.0154400
0.1000000 -.0178700
0.1500000 -.0226500
0.2000000 -.0273100
0.2500000 -.0311800
0.3000000 -.0342500
0.3500000 -.0364200
0.4000000 -.0376300
0.4500000 -.0378200
0.5000000 -.0369600
0.5500000 -.0348700
0.6000000 -.0317400
0.6500000 -.0278700
0.7000000 -.0238900
0.7500000 -.0199100
0.8000000 -.0159300
0.8500000 -.0119400
0.9000000 -.0079600
0.9500000 -.0039800
1.0000000 0.0000000
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Polars for KC-135 BL200.76 AIRFOIL (kc135c-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| kc135c-il | 50,000 | 9 | 34.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 50,000 | 5 | 34.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135c-il | 100,000 | 9 | 52 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 100,000 | 5 | 50.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135c-il | 200,000 | 9 | 71.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 200,000 | 5 | 66 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135c-il | 500,000 | 9 | 91.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 500,000 | 5 | 73.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135c-il | 1,000,000 | 9 | 100.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 1,000,000 | 5 | 78.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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