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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(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 |
(s809-nr) NREL's S809 Airfoil | NREL HAWT airfoil S809 primary 21.0% Re=2.0E+6 Clmax(S)=1.00 Restrained max lift coef Max thickness 21% at 39.5% chord Max camber 1% at 82.3% chord | Remove Airfoil details Airfoil plotter |
(ht22-il) HT22 | Drela HT22 airfoil Max thickness 5.1% at 19.1% chord Max camber 1.1% at 22.7% chord | Remove Airfoil details Airfoil plotter |
(sc2110-il) SIKORSKY SC2110 AIRFOIL | Sikorsky/Lednicer & Owen SC2110 rotorcraft airfoil (SC5410) Max thickness 9.9% at 37.7% chord Max camber 1.9% at 15.7% chord | Remove Airfoil details Airfoil plotter |
(e664-il) EPPLER 664 AIRFOIL | Eppler E664 variable geometry sailplane airfoil Max thickness 16.6% at 45.6% chord Max camber 2.6% at 40.7% 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 (hq309-il,s809-nr,ht22-il,sc2110-il,e664-il,hsnlf213-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| s809-nr | 50,000 | 9 | 15.5 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 50,000 | 5 | 13.9 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 100,000 | 9 | 23.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 100,000 | 5 | 26.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 200,000 | 9 | 51.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 200,000 | 5 | 53.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 500,000 | 9 | 81.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 500,000 | 5 | 75.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 1,000,000 | 9 | 100.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 1,000,000 | 5 | 89.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht22-il | 50,000 | 9 | 25.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht22-il | 50,000 | 5 | 27.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht22-il | 100,000 | 9 | 35 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht22-il | 100,000 | 5 | 36.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht22-il | 200,000 | 9 | 46 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht22-il | 200,000 | 5 | 46.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht22-il | 500,000 | 9 | 60.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht22-il | 500,000 | 5 | 63.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht22-il | 1,000,000 | 9 | 75.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht22-il | 1,000,000 | 5 | 78.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc2110-il | 50,000 | 9 | 26.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc2110-il | 50,000 | 5 | 27.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc2110-il | 100,000 | 9 | 34.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc2110-il | 100,000 | 5 | 38.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc2110-il | 200,000 | 9 | 47.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc2110-il | 200,000 | 5 | 52.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc2110-il | 500,000 | 9 | 71.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc2110-il | 500,000 | 5 | 74.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc2110-il | 1,000,000 | 9 | 91.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc2110-il | 1,000,000 | 5 | 92.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e664-il | 50,000 | 9 | 19.3 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 50,000 | 5 | 19.7 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e664-il | 100,000 | 9 | 39.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 100,000 | 5 | 33.2 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e664-il | 200,000 | 9 | 57.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 200,000 | 5 | 58.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e664-il | 500,000 | 9 | 90.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 500,000 | 5 | 90.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e664-il | 1,000,000 | 9 | 120.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e664-il | 1,000,000 | 5 | 111.2 at α=3.75° | 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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