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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(pmc19sm-il) PMC19 Smoothed | PMC19 Max thickness 9.2% at 34.2% chord Max camber 2.1% at 17.5% chord | Remove Airfoil details Airfoil plotter |
(p51droot-il) P-51D ROOT (BL17.5) AIRFOIL | P-51D root (BL17.5) airfoil Max thickness 16.5% at 38.9% chord Max camber 1.3% at 68.3% chord | Remove Airfoil details Airfoil plotter |
(p51dtip-il) P-51D TIP (BL215) AIRFOIL | P-51D tip (BL215) airfoil Max thickness 11.4% at 46.3% chord Max camber 1.3% at 46.3% chord | Remove Airfoil details Airfoil plotter |
(p51hroot-il) NACA 66 | NACA 66 Max thickness 15.5% at 45% chord Max camber 1.3% at 47.5% chord | Remove Airfoil details Airfoil plotter |
(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 |
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Polars for (pmc19sm-il,p51droot-il,p51dtip-il,p51hroot-il,psu94097-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| pmc19sm-il | 50,000 | 9 | 28 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pmc19sm-il | 50,000 | 5 | 32.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pmc19sm-il | 100,000 | 9 | 44.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pmc19sm-il | 100,000 | 5 | 45 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pmc19sm-il | 200,000 | 9 | 58.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pmc19sm-il | 200,000 | 5 | 57.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pmc19sm-il | 500,000 | 9 | 79 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pmc19sm-il | 500,000 | 5 | 74 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pmc19sm-il | 1,000,000 | 9 | 93.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pmc19sm-il | 1,000,000 | 5 | 82.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51droot-il | 50,000 | 9 | 28 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 50,000 | 5 | 23.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51droot-il | 100,000 | 9 | 46.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 100,000 | 5 | 43.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51droot-il | 200,000 | 9 | 62.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 200,000 | 5 | 57.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51droot-il | 500,000 | 9 | 81.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 500,000 | 5 | 71.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51droot-il | 1,000,000 | 9 | 92.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 1,000,000 | 5 | 79.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 50,000 | 9 | 22.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 50,000 | 5 | 23.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 100,000 | 9 | 40.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 100,000 | 5 | 35.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 200,000 | 9 | 54.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 200,000 | 5 | 49.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 500,000 | 9 | 74.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 500,000 | 5 | 63.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 1,000,000 | 9 | 89.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 1,000,000 | 5 | 68.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51hroot-il | 50,000 | 9 | 20.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51hroot-il | 50,000 | 5 | 19.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51hroot-il | 100,000 | 9 | 32.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51hroot-il | 100,000 | 5 | 27.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51hroot-il | 200,000 | 9 | 42.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51hroot-il | 200,000 | 5 | 43.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51hroot-il | 500,000 | 9 | 67.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51hroot-il | 500,000 | 5 | 55.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51hroot-il | 1,000,000 | 9 | 70.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51hroot-il | 1,000,000 | 5 | 46.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
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