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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(clarym18-il) CLARK YM-18 AIRFOIL | CLARK YM18 airfoil Max thickness 18% at 29.6% chord Max camber 3.6% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(cp-080-050-gn) Cambered plate C=8% T=5% R=1.6 | HAWT pipe blade with coordinates based on top surface. Camber=8% Wall thickness=5% Radius=1.603 Max thickness 8.4% at 5% chord Max camber 5.3% at 47% chord | Remove Airfoil details Airfoil plotter |
(clarym15-il) CLARK YM-15 AIRFOIL | CLARK YM15 airfoil Max thickness 15% at 29.6% chord Max camber 3.6% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(coanda1-il) Coanda 1 | Coanda 1 airfoil Max thickness 5.7% at 30% chord Max camber 2.9% at 40% 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 |
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Polars for (clarym18-il,cp-080-050-gn,clarym15-il,coanda1-il,hq3013-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| clarym18-il | 50,000 | 9 | 7.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 50,000 | 5 | 25.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 100,000 | 9 | 43.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 100,000 | 5 | 43.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 200,000 | 9 | 60.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 200,000 | 5 | 56 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 500,000 | 9 | 77.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 500,000 | 5 | 73.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 1,000,000 | 9 | 96.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 1,000,000 | 5 | 93.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 50,000 | 9 | 25.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 50,000 | 5 | 24.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 50,000 | 1 | 22 at α=11° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-080-050-gn | 100,000 | 9 | 30 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 100,000 | 5 | 29.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 100,000 | 1 | 30.1 at α=8° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-080-050-gn | 200,000 | 9 | 33.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 200,000 | 5 | 34.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 200,000 | 1 | 37.7 at α=7.75° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-080-050-gn | 500,000 | 9 | 41.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 500,000 | 5 | 44.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 500,000 | 1 | 51.4 at α=8° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-080-050-gn | 1,000,000 | 9 | 50.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 1,000,000 | 5 | 57.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 1,000,000 | 1 | 64.2 at α=8.5° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| clarym15-il | 50,000 | 9 | 12.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 50,000 | 5 | 31 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 100,000 | 9 | 47.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 100,000 | 5 | 48.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 200,000 | 9 | 66.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 200,000 | 5 | 62.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 500,000 | 9 | 88.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 500,000 | 5 | 84.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym15-il | 1,000,000 | 9 | 109.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym15-il | 1,000,000 | 5 | 105.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda1-il | 50,000 | 9 | 38 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 50,000 | 5 | 37.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda1-il | 100,000 | 9 | 54.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 100,000 | 5 | 47.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda1-il | 200,000 | 9 | 60.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 200,000 | 5 | 45.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda1-il | 500,000 | 9 | 63.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 500,000 | 5 | 51.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda1-il | 1,000,000 | 9 | 60.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda1-il | 1,000,000 | 5 | 57.7 at α=4.5° | 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 | |
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