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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(hq3510-il) HQ 3.5/10 AIRFOIL | Quabeck HQ 3.5/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 3.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq3514-il) HQ 3.5/14 AIRFOIL | Quabeck HQ 3.5/14 R/C sailplane airfoil Max thickness 14% at 35% chord Max camber 3.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq3015-il) HQ 3.0/15 AIRFOIL | Quabeck HQ 3.0/15 R/C sailplane airfoil Max thickness 15% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq1010-il) HQ 1.0/10 AIRFOIL | Quabeck HQ 1.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 1% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq3013-il) HQ 3.0/13 AIRFOIL | Quabeck HQ 3.0/13 R/C sailplane airfoil Max thickness 13% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq3014-il) HQ 3.0/14 AIRFOIL | Quabeck HQ 3.0/14 R/C sailplane airfoil Max thickness 14% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
(hq259b-il) HQ 2.5/9 B AIRFOIL | Quabeck HQ 2.5/9 B R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 2.5% at 55% chord | Remove Airfoil details Airfoil plotter |
(tsagi-r-3a-il) TsAGI R-3a (12%) | TsAGI R-3a used on Russian ultra light aircraft (12%). Max thickness 12.1% at 23.1% chord Max camber 3.1% at 24.1% 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 (hq3510-il,hq3514-il,hq3015-il,hq1010-il,hq3013-il,hq3014-il,hq259b-il,tsagi-r-3a-il,hsnlf213-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq3510-il | 50,000 | 9 | 37.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3510-il | 50,000 | 5 | 40.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3510-il | 100,000 | 9 | 61.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3510-il | 100,000 | 5 | 60.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3510-il | 200,000 | 9 | 87 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3510-il | 200,000 | 5 | 80.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3510-il | 500,000 | 9 | 119 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3510-il | 500,000 | 5 | 95.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3510-il | 1,000,000 | 9 | 129.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3510-il | 1,000,000 | 5 | 106.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 50,000 | 9 | 29.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 50,000 | 5 | 33.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 100,000 | 9 | 55.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 100,000 | 5 | 54.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 200,000 | 9 | 80 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 200,000 | 5 | 71.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 500,000 | 9 | 100.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 500,000 | 5 | 86.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 1,000,000 | 9 | 112.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 1,000,000 | 5 | 99.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3015-il | 50,000 | 9 | 25.8 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 50,000 | 5 | 30.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3015-il | 100,000 | 9 | 52.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 100,000 | 5 | 51.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3015-il | 200,000 | 9 | 75.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 200,000 | 5 | 67.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3015-il | 500,000 | 9 | 97.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 500,000 | 5 | 84 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3015-il | 1,000,000 | 9 | 111.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3015-il | 1,000,000 | 5 | 95.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 50,000 | 9 | 32.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 50,000 | 5 | 32.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 100,000 | 9 | 47.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 100,000 | 5 | 45.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 200,000 | 9 | 63.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 200,000 | 5 | 55.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 500,000 | 9 | 79.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 500,000 | 5 | 68.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 1,000,000 | 9 | 85.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 1,000,000 | 5 | 78 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3013-il | 50,000 | 9 | 32.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3013-il | 50,000 | 5 | 35.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3013-il | 100,000 | 9 | 55.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3013-il | 100,000 | 5 | 55.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3013-il | 200,000 | 9 | 79.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3013-il | 200,000 | 5 | 73.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3013-il | 500,000 | 9 | 106 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3013-il | 500,000 | 5 | 86.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3013-il | 1,000,000 | 9 | 115.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3013-il | 1,000,000 | 5 | 97.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3014-il | 50,000 | 9 | 30.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3014-il | 50,000 | 5 | 33 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3014-il | 100,000 | 9 | 54.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3014-il | 100,000 | 5 | 53.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3014-il | 200,000 | 9 | 77.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3014-il | 200,000 | 5 | 70.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3014-il | 500,000 | 9 | 99.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3014-il | 500,000 | 5 | 85.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3014-il | 1,000,000 | 9 | 113.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3014-il | 1,000,000 | 5 | 96.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 50,000 | 9 | 39 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 50,000 | 5 | 39.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 100,000 | 9 | 58.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 100,000 | 5 | 56.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 200,000 | 9 | 79.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 200,000 | 5 | 73.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 500,000 | 9 | 105.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 500,000 | 5 | 84.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq259b-il | 1,000,000 | 9 | 112.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq259b-il | 1,000,000 | 5 | 91.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 50,000 | 9 | 16.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 50,000 | 5 | 25.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 100,000 | 9 | 33 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 100,000 | 5 | 43.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 200,000 | 9 | 56.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 200,000 | 5 | 60.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 500,000 | 9 | 86.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 500,000 | 5 | 88.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 1,000,000 | 9 | 112.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi-r-3a-il | 1,000,000 | 5 | 108.9 at α=8.25° | 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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