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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(ht23-il) HT23 | Drela HT23 airfoil Max thickness 6.5% at 20.8% chord Max camber 1.1% at 22.6% chord | Remove Airfoil details Airfoil plotter |
(hq309-il) HQ 3.0/9 AIRFOIL | Quabeck HQ 3.0/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
(hsnlf213-il) HSNLF(1)-0213 AIRFOIL | NASA/Langley HSNLF(1)-0213 high speed natural laminar flow airfoil Max thickness 13.3% at 42.4% chord Max camber 1.4% at 32.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ht23-il,hq309-il,hsnlf213-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ht23-il | 50,000 | 9 | 24.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 50,000 | 5 | 29 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 100,000 | 9 | 37.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 100,000 | 5 | 39.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 200,000 | 9 | 50.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 200,000 | 5 | 50.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 500,000 | 9 | 67.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 500,000 | 5 | 65.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht23-il | 1,000,000 | 9 | 79.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht23-il | 1,000,000 | 5 | 79.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq309-il | 50,000 | 9 | 39.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 50,000 | 5 | 41.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq309-il | 100,000 | 9 | 61.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 100,000 | 5 | 59.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq309-il | 200,000 | 9 | 84.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 200,000 | 5 | 78.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq309-il | 500,000 | 9 | 114.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 500,000 | 5 | 96.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq309-il | 1,000,000 | 9 | 132.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq309-il | 1,000,000 | 5 | 101.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hsnlf213-il | 50,000 | 9 | 28.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 50,000 | 5 | 27.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hsnlf213-il | 100,000 | 9 | 46 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 100,000 | 5 | 37.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hsnlf213-il | 200,000 | 9 | 53.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 200,000 | 5 | 49.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hsnlf213-il | 500,000 | 9 | 70.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 500,000 | 5 | 59.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hsnlf213-il | 1,000,000 | 9 | 78.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hsnlf213-il | 1,000,000 | 5 | 67.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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