AH-7-47-6 AIRFOIL (ah7476-il)
AH-7-47-6 AIRFOIL - Althaus AH 7-476 airfoil
Details | Dat file | Parser | |
(ah7476-il) AH-7-47-6 AIRFOIL Althaus AH 7-476 airfoil Max thickness 5.9% at 20% chord. Max camber 6.2% at 50% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
AH-7-47-6 AIRFOIL 16. 16. 0.0000000 0.0000000 0.0124200 0.0180600 0.0248800 0.0271100 0.0498200 0.0392200 0.0747800 0.0488400 0.0997500 0.0564500 0.1497000 0.0676700 0.1996600 0.0759000 0.2996100 0.0858500 0.3996000 0.0878000 0.4996100 0.0862500 0.5996400 0.0807000 0.6996800 0.0706500 0.7997500 0.0546000 0.8998500 0.0340500 1.0000000 0.0035000 0.0000000 0.0000000 0.0125400 -.0079400 0.0250300 -.0058900 0.0500100 -.0032700 0.0750000 0.0003400 0.0999800 0.0034500 0.1499500 0.0106700 0.1999200 0.0169000 0.2998800 0.0273500 0.3998500 0.0343000 0.4998300 0.0377500 0.5998300 0.0387000 0.6998400 0.0361500 0.7998700 0.0291000 0.8999299 0.0160500 1.0000000 -.0035000 |
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Polars for AH-7-47-6 AIRFOIL (ah7476-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
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ah7476-il | 50,000 | 9 | 48.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
ah7476-il | 50,000 | 5 | 48.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
ah7476-il | 100,000 | 9 | 75.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
ah7476-il | 100,000 | 5 | 74.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
ah7476-il | 200,000 | 9 | 107.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
ah7476-il | 200,000 | 5 | 103.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
ah7476-il | 500,000 | 9 | 148.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
ah7476-il | 500,000 | 5 | 110.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
ah7476-il | 1,000,000 | 9 | 138.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
ah7476-il | 1,000,000 | 5 | 112.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
Reynolds number calculator |