UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il)
UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL - University of Glasgow GU 25-5(11)8 canard airfoil (Quickie
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(gu255118-il) UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL University of Glasgow GU 25-5(11)8 canard airfoil (Quickie Max thickness 20% at 40% chord. Max camber 7.1% at 45% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL 24. 24. 0.000 0.00000 0.005 0.01552 0.025 0.04082 0.050 0.06199 0.075 0.07876 0.100 0.09291 0.150 0.11593 0.200 0.13388 0.250 0.14787 0.300 0.15844 0.350 0.16582 0.400 0.17003 0.450 0.17084 0.500 0.16750 0.550 0.15800 0.600 0.14434 0.650 0.12815 0.700 0.11037 0.750 0.09173 0.800 0.07282 0.850 0.05413 0.900 0.03602 0.950 0.01815 1.000 0.00000 0.000 0.00000 0.005 -0.00964 0.025 -0.01819 0.050 -0.02262 0.075 -0.02532 0.100 -0.02720 0.150 -0.02956 0.200 -0.03080 0.250 -0.03133 0.300 -0.03131 0.350 -0.03081 0.400 -0.02985 0.450 -0.02826 0.500 -0.02616 0.550 -0.02381 0.600 -0.02131 0.650 -0.01875 0.700 -0.01621 0.750 -0.01374 0.800 -0.01137 0.850 -0.00913 0.900 -0.00694 0.950 -0.00410 1.000 0.00000 25 0.0408 |
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Polars for UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL (gu255118-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| gu255118-il | 50,000 | 9 | 3.9 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gu255118-il | 50,000 | 5 | 6.7 at α=17.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gu255118-il | 100,000 | 9 | 11.2 at α=18.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gu255118-il | 100,000 | 5 | 10.7 at α=17° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gu255118-il | 200,000 | 9 | 17.4 at α=16.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gu255118-il | 200,000 | 5 | 38.3 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gu255118-il | 500,000 | 9 | 63.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gu255118-il | 500,000 | 5 | 93.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gu255118-il | 1,000,000 | 9 | 136.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gu255118-il | 1,000,000 | 5 | 137.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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