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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(psu94097-il) PSU 94-097 (AIAA 2001-2478) | Maughmer PSU 94-097 winglet airfoil Max thickness 9.7% at 32.3% chord Max camber 4% at 46.3% chord | Remove Airfoil details Airfoil plotter |
(npl9615-il) NPL 9615 AIRFOIL | NPL 9615 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord | Remove Airfoil details Airfoil plotter |
(r1080-il) RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL | Roncz 1080 Voyager inner aft wing airfoil Max thickness 18% at 40% chord Max camber 3.3% at 40% chord | Remove Airfoil details Airfoil plotter |
(oaf102-il) OAF102 AIRFOIL | ONERA/Aerospatiale OAF102 Fenestron airfoil Max thickness 10.2% at 28.7% chord Max camber 3.6% at 53.1% chord | Remove Airfoil details Airfoil plotter |
(pt40-il) PT40 | Great Plane PT-40 trainer airfoil Max thickness 11.6% at 27.1% chord Max camber 2.9% at 41.6% chord | Remove Airfoil details Airfoil plotter |
(oaf128-il) OAF128 AIRFOIL | ONERA/Aerospatiale OAF128 Fenestron airfoil Max thickness 12.8% at 23.2% chord Max camber 1% at 43.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (psu94097-il,npl9615-il,r1080-il,oaf102-il,pt40-il,oaf128-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| psu94097-il | 50,000 | 9 | 39.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| psu94097-il | 50,000 | 5 | 41.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| psu94097-il | 100,000 | 9 | 64 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| psu94097-il | 100,000 | 5 | 64.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| psu94097-il | 200,000 | 9 | 90.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| psu94097-il | 200,000 | 5 | 86.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| psu94097-il | 500,000 | 9 | 126.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| psu94097-il | 500,000 | 5 | 112.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| psu94097-il | 1,000,000 | 9 | 150.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| psu94097-il | 1,000,000 | 5 | 127.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 50,000 | 9 | 29 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 50,000 | 5 | 30.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 100,000 | 9 | 43.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 100,000 | 5 | 42.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 200,000 | 9 | 56.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 200,000 | 5 | 52.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 500,000 | 9 | 70.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 500,000 | 5 | 68.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9615-il | 1,000,000 | 9 | 84.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9615-il | 1,000,000 | 5 | 77.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1080-il | 50,000 | 9 | 5.8 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 50,000 | 5 | 13.3 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1080-il | 100,000 | 9 | 28 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 100,000 | 5 | 22.9 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1080-il | 200,000 | 9 | 55.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 200,000 | 5 | 55.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1080-il | 500,000 | 9 | 106.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 500,000 | 5 | 102.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| r1080-il | 1,000,000 | 9 | 139.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| r1080-il | 1,000,000 | 5 | 127 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 50,000 | 9 | 40.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 50,000 | 5 | 41.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 100,000 | 9 | 61.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 100,000 | 5 | 60.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 200,000 | 9 | 82.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 200,000 | 5 | 77.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 500,000 | 9 | 107.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 500,000 | 5 | 86.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf102-il | 1,000,000 | 9 | 114 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf102-il | 1,000,000 | 5 | 92 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 50,000 | 9 | 32.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 50,000 | 5 | 33.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 100,000 | 9 | 48.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 100,000 | 5 | 46.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 200,000 | 9 | 64.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 200,000 | 5 | 57.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 500,000 | 9 | 78.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 500,000 | 5 | 76.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 1,000,000 | 9 | 95 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 1,000,000 | 5 | 89.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf128-il | 50,000 | 9 | 24.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 50,000 | 5 | 31.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf128-il | 100,000 | 9 | 41.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 100,000 | 5 | 43.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf128-il | 200,000 | 9 | 56.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 200,000 | 5 | 55.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf128-il | 500,000 | 9 | 74.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 500,000 | 5 | 71 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf128-il | 1,000,000 | 9 | 85.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf128-il | 1,000,000 | 5 | 85.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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