Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(ah88k136-il) AH 88-K-136/16 | Althaus AH 88-K-136/16 airfoil for use with flaps (K) Max thickness 13.5% at 44.9% chord Max camber 3% at 41.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (ah88k136-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah88k136-il | 50,000 | 9 | 21.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k136-il | 50,000 | 5 | 21.8 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k136-il | 100,000 | 9 | 40.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k136-il | 100,000 | 5 | 38.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k136-il | 200,000 | 9 | 73.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k136-il | 200,000 | 5 | 72.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k136-il | 500,000 | 9 | 113.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k136-il | 500,000 | 5 | 87.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah88k136-il | 1,000,000 | 9 | 113.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah88k136-il | 1,000,000 | 5 | 95.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||