Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(l188root-il) LOCKHEED L-188 ROOT AIRFOIL | Lockheed L-188/P-3 root airfoil NACA 0014 -1.10 40/1.051 Cli=.3 a=.8 Max thickness 14% at 41.3% chord Max camber 2% at 51.7% chord | Remove Airfoil details Airfoil plotter |
(lrn1007-il) lrn1007 | LRN(1)-1007 low Reynolds number airfoil Max thickness 7.3% at 39.8% chord Max camber 5.9% at 44.6% chord | Remove Airfoil details Airfoil plotter |
(n2h15-il) NACA 2-H-15 AIRFOIL | NACA 2-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 4.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (l188root-il,lrn1007-il,n2h15-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| l188root-il | 50,000 | 9 | 32.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 50,000 | 5 | 29.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188root-il | 100,000 | 9 | 51.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 100,000 | 5 | 48.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188root-il | 200,000 | 9 | 72.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 200,000 | 5 | 65.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188root-il | 500,000 | 9 | 94.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 500,000 | 5 | 75.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188root-il | 1,000,000 | 9 | 104 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188root-il | 1,000,000 | 5 | 79.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 50,000 | 9 | 30.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 50,000 | 5 | 35.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 100,000 | 9 | 51.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 100,000 | 5 | 55.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 200,000 | 9 | 81.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 200,000 | 5 | 98.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 500,000 | 9 | 125.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1007-il | 500,000 | 5 | 150.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1007-il | 1,000,000 | 9 | 127.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 50,000 | 9 | 18.1 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 50,000 | 5 | 13.4 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 100,000 | 9 | 20 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 100,000 | 5 | 20.3 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 200,000 | 9 | 34.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 200,000 | 5 | 38.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 500,000 | 9 | 110.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 500,000 | 5 | 107.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n2h15-il | 1,000,000 | 9 | 145.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n2h15-il | 1,000,000 | 5 | 122.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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