UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT (ua79sff-il)
UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT - University of Alberta/Marsden UA 79-SF-187 sailplane airfoil FLAP
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(ua79sff-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT University of Alberta/Marsden UA 79-SF-187 sailplane airfoil FLAP Max thickness 8.7% at 73.1% chord. Max camber 3.4% at 78.1% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT
20.0 20.0
0.650000 -.018400
0.654800 0.007200
0.665100 0.026400
0.682300 0.042400
0.697200 0.050800
0.716900 0.057800
0.730700 0.061100
0.747600 0.063400
0.766000 0.064400
0.780800 0.063600
0.795800 0.061800
0.811700 0.058400
0.853500 0.045000
0.890900 0.033300
0.923400 0.023000
0.950500 0.015000
0.971900 0.008500
0.987500 0.003700
0.996900 0.001000
1.000000 0.000000
0.650000 -.018400
0.654800 -.029800
0.665100 -.034100
0.682300 -.032900
0.697200 -.031100
0.716900 -.028100
0.730700 -.025700
0.747600 -.023400
0.766000 -.020800
0.780800 -.018300
0.795800 -.016500
0.811700 -.013700
0.853500 -.007900
0.890900 -.003300
0.923400 -.000300
0.950500 0.000600
0.971900 0.000900
0.987500 0.000700
0.996900 0.000300
1.000000 0.000000
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Polars for UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT (ua79sff-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ua79sff-il | 50,000 | 9 | 3.4 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 50,000 | 5 | 3.5 at α=19.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 100,000 | 9 | 3.6 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 100,000 | 5 | 4.1 at α=18.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 200,000 | 9 | 3.8 at α=19.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 200,000 | 5 | 5.1 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 500,000 | 9 | 6.4 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 500,000 | 5 | 25.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sff-il | 1,000,000 | 9 | 60.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sff-il | 1,000,000 | 5 | 62 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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