S8066 (10% version of S8065 w/ lower surface aerodynamically similar) (s8066-il)
S8066 (10% version of S8065 w/ lower surface aerodynamically similar) - Selig airfoil for Q-40 pylon racing (10%).
| Details | Dat file | Parser | |
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(s8066-il) S8066 (10% version of S8065 w/ lower surface aerodynamically similar) Selig airfoil for Q-40 pylon racing (10%). Max thickness 10% at 37.7% chord. Max camber 0.8% at 56.3% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S8066 (10% version of S8065 w/ lower surface aerodynamically similar)
1.000000000000000000 0.000000000000000000
0.998057840676878200 0.000166937137092193
0.992416288358743700 0.000736101176910097
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0.970646747337505600 0.003152504369279306
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0.954155536243004000 -0.002449116895450627
0.970080315650033300 -0.001463440916806641
0.982789320394193000 -0.000667762033907935
0.992188134694531200 -0.000159936244795328
0.998019447354635500 0.000009663562748016
1.000000000000000000 0.000000000000000004
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Polars for S8066 (10% version of S8065 w/ lower surface aerodynamically similar) (s8066-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s8066-il | 50,000 | 9 | 32.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8066-il | 50,000 | 5 | 31.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8066-il | 100,000 | 9 | 47.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8066-il | 100,000 | 5 | 44.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8066-il | 200,000 | 9 | 64.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8066-il | 200,000 | 5 | 54.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8066-il | 500,000 | 9 | 75 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8066-il | 500,000 | 5 | 61.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8066-il | 1,000,000 | 9 | 81.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8066-il | 1,000,000 | 5 | 73.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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