BOEING 737 ROOT AIRFOIL (b737a-il)
BOEING 737 ROOT AIRFOIL - Boeing Commercial Airplane Company model 737 airfoils
| Details | Dat file | Parser | |
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(b737a-il) BOEING 737 ROOT AIRFOIL Boeing Commercial Airplane Company model 737 airfoils Max thickness 15.4% at 19.6% chord. Max camber 0.2% at 5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
BOEING 737 ROOT AIRFOIL
23. 23.
0.000000 0.017700
0.002300 0.030900
0.005000 0.037200
0.007600 0.041500
0.014300 0.049900
0.024900 0.058200
0.049500 0.073000
0.074000 0.081400
0.099000 0.086600
0.153000 0.090700
0.196100 0.090500
0.250400 0.088700
0.309400 0.085800
0.352000 0.083300
0.391900 0.080400
0.447700 0.075600
0.503400 0.069600
0.559300 0.062600
0.596500 0.057500
0.648800 0.049800
0.835100 0.022400
0.910900 0.013200
1.000000 0.000300
0.000000 0.017700
0.002200 0.003800
0.004900 -0.001800
0.007200 -0.005300
0.011900 -0.010600
0.024300 -0.020400
0.048600 -0.034200
0.071600 -0.045700
0.097900 -0.051600
0.148800 -0.060700
0.195300 -0.063200
0.250100 -0.063200
0.294500 -0.062600
0.357900 -0.061000
0.396500 -0.059500
0.454300 -0.056300
0.505000 -0.052700
0.555600 -0.048200
0.606300 -0.042700
0.648500 -0.037500
0.831700 -0.014900
0.941000 -0.005300
1.000000 -0.000300
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Polars for BOEING 737 ROOT AIRFOIL (b737a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| b737a-il | 50,000 | 9 | 16.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737a-il | 50,000 | 5 | 19.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737a-il | 100,000 | 9 | 23.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737a-il | 100,000 | 5 | 30.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737a-il | 200,000 | 9 | 38.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737a-il | 200,000 | 5 | 46.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737a-il | 500,000 | 9 | 67.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737a-il | 500,000 | 5 | 68.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737a-il | 1,000,000 | 9 | 85.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737a-il | 1,000,000 | 5 | 79.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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