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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(hs1606-il) HAM-STD HS1-606 AIRFOIL | HS1 family of prop airfoils from US Patent No. 4 Max thickness 6% at 18% chord Max camber 4.4% at 46% chord | Remove Airfoil details Airfoil plotter |
(ht05-il) HT05 | Drela HT05 airfoil Max thickness 4.8% at 17.1% chord Max camber 0% at 63.3% chord | Remove Airfoil details Airfoil plotter |
(hq2512-il) HQ 2.5/12 AIRFOIL | Quabeck HQ 2.5/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 2.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq3011-il) HQ 3.0/11 AIRFOIL | Quabeck HQ 3.0/11 R/C sailplane airfoil Max thickness 11% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hs1606-il,ht05-il,hq2512-il,hq3011-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hs1606-il | 50,000 | 9 | 45.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1606-il | 50,000 | 5 | 45 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1606-il | 100,000 | 9 | 68.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1606-il | 100,000 | 5 | 66.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1606-il | 200,000 | 9 | 95.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1606-il | 200,000 | 5 | 90.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1606-il | 500,000 | 9 | 133.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1606-il | 500,000 | 5 | 121.9 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hs1606-il | 1,000,000 | 9 | 160.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hs1606-il | 1,000,000 | 5 | 108.4 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 50,000 | 9 | 19.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 50,000 | 5 | 19.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 100,000 | 9 | 24.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 100,000 | 5 | 26.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 200,000 | 9 | 31.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 200,000 | 5 | 34.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 500,000 | 9 | 44.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 500,000 | 5 | 49.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 1,000,000 | 9 | 57.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 1,000,000 | 5 | 63.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 50,000 | 9 | 33.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 50,000 | 5 | 36.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 100,000 | 9 | 55.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 100,000 | 5 | 53.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 200,000 | 9 | 76.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 200,000 | 5 | 70.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 500,000 | 9 | 100.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 500,000 | 5 | 83.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 1,000,000 | 9 | 108.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 1,000,000 | 5 | 92.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3011-il | 50,000 | 9 | 36.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 50,000 | 5 | 38.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3011-il | 100,000 | 9 | 58.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 100,000 | 5 | 57.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3011-il | 200,000 | 9 | 81.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 200,000 | 5 | 75.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3011-il | 500,000 | 9 | 111.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 500,000 | 5 | 92.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3011-il | 1,000,000 | 9 | 124.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3011-il | 1,000,000 | 5 | 101.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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