UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL (ua79sf18-il)
UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL - University of Alberta/Marsden UA 79-SF-187 FLAPPED sailplane airfoil
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(ua79sf18-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL University of Alberta/Marsden UA 79-SF-187 FLAPPED sailplane airfoil Max thickness 18.8% at 42.8% chord. Max camber 3.7% at 63.4% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL
38.0 37.0
0.000000 0.000000
0.002400 0.005600
0.009500 0.015800
0.021200 0.027900
0.037500 0.040000
0.058100 0.052400
0.082800 0.064400
0.111200 0.076000
0.143100 0.086800
0.178100 0.096700
0.215800 0.105500
0.255600 0.112900
0.297300 0.119100
0.340200 0.123900
0.383900 0.127400
0.427800 0.129300
0.471500 0.129900
0.514500 0.128900
0.556100 0.126500
0.596000 0.122900
0.633600 0.117100
0.668600 0.110500
0.700500 0.101600
0.729000 0.092400
0.753600 0.082900
0.774200 0.075000
0.790500 0.068500
0.802300 0.063900
0.809400 0.061200
0.811700 0.060300
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
0.000000 0.000000
0.002400 -.003400
0.009500 -.008900
0.021200 -.014700
0.037500 -.020500
0.058100 -.026300
0.082800 -.031800
0.111200 -.037100
0.143100 -.041900
0.178100 -.046200
0.215800 -.049900
0.255600 -.053000
0.297300 -.055300
0.340200 -.057100
0.383900 -.058100
0.427800 -.058400
0.471500 -.057700
0.514500 -.056100
0.556100 -.053400
0.596000 -.049500
0.633600 -.042400
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 (ua79sf18-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ua79sf18-il | 50,000 | 9 | 15 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 50,000 | 5 | 15.2 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sf18-il | 100,000 | 9 | 24.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 100,000 | 5 | 23.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sf18-il | 200,000 | 9 | 37.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 200,000 | 5 | 35 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sf18-il | 500,000 | 9 | 65 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 500,000 | 5 | 75.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ua79sf18-il | 1,000,000 | 9 | 133.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ua79sf18-il | 1,000,000 | 5 | 114.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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