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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(r1082-il) RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL | Roncz 1082 Voyager root outer aft wing airfoil Max thickness 18% at 40% chord Max camber 3.4% at 40% chord | Remove Airfoil details Airfoil plotter |
(giiil-il) GIII BL387 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35.1% chord Max camber 1.6% at 25.1% chord | Remove Airfoil details Airfoil plotter |
(doa5-il) DORNIER A-5 AIRFOIL | Dornier A-5 airfoil (reconstruction) (DO 228 wing) Max thickness 16.2% at 40.1% chord Max camber 2.5% at 76% chord | Remove Airfoil details Airfoil plotter |
(hq1585-il) HQ 1.5/8.5 AIRFOIL | Quabeck HQ 1.5/8.5 R/C sailplane airfoil Max thickness 8.6% at 35% chord Max camber 1.5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (r1082-il,giiil-il,doa5-il,hq1585-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| r1082-il | 50,000 | 9 | 4.2 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 50,000 | 5 | 12.1 at α=14.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082-il | 100,000 | 9 | 25.4 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 100,000 | 5 | 21.5 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082-il | 200,000 | 9 | 60.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 200,000 | 5 | 61.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082-il | 500,000 | 9 | 105.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 500,000 | 5 | 102.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1082-il | 1,000,000 | 9 | 136.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1082-il | 1,000,000 | 5 | 127.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 50,000 | 9 | 31.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 50,000 | 5 | 31.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 100,000 | 9 | 45 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 100,000 | 5 | 42.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 200,000 | 9 | 57.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 200,000 | 5 | 51.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 500,000 | 9 | 72.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 500,000 | 5 | 67.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 1,000,000 | 9 | 82 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 1,000,000 | 5 | 82.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| doa5-il | 50,000 | 9 | 29.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 50,000 | 5 | 25.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| doa5-il | 100,000 | 9 | 41.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 100,000 | 5 | 35.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| doa5-il | 200,000 | 9 | 52 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 200,000 | 5 | 49.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| doa5-il | 500,000 | 9 | 75.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 500,000 | 5 | 59 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| doa5-il | 1,000,000 | 9 | 87.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| doa5-il | 1,000,000 | 5 | 68.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 50,000 | 9 | 35.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 50,000 | 5 | 35.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 100,000 | 9 | 51.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 100,000 | 5 | 48.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 200,000 | 9 | 67.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 200,000 | 5 | 58.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 500,000 | 9 | 84.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 500,000 | 5 | 67.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1585-il | 1,000,000 | 9 | 85.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1585-il | 1,000,000 | 5 | 80.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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