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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(oa213-il) ONERA OA213 AIRFOIL | ONERA/Aerospatiale OA213 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 12.6% at 32.5% chord Max camber 3.3% at 25% chord | Remove Airfoil details Airfoil plotter |
(hq09-il) HQ 0/9 AIRFOIL | Quabeck HQ 0/9 R/C sailplane airfoil Max thickness 8.1% at 33.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(l7769-il) LISSAMAN 7769 AIRFOIL | Lissaman 7769 human powered aircraft airfoil Max thickness 11% at 30% chord Max camber 4.4% at 30% chord | Remove Airfoil details Airfoil plotter |
(l188tip-il) LOCKHEED L-188 TIP AIRFOIL | Lockheed L-188/P-3 tip airfoil NACA 0012 -1.10 40/1.051 Cli=.4 a=.8 Max thickness 12% at 41.3% chord Max camber 2.7% at 51.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (oa213-il,hq09-il,l7769-il,l188tip-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| oa213-il | 50,000 | 9 | 26.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 50,000 | 5 | 29.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 100,000 | 9 | 41.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 100,000 | 5 | 41.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 200,000 | 9 | 54 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 200,000 | 5 | 54.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 500,000 | 9 | 75.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 500,000 | 5 | 75.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oa213-il | 1,000,000 | 9 | 95.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oa213-il | 1,000,000 | 5 | 93.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 50,000 | 9 | 27.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 50,000 | 5 | 26 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 100,000 | 9 | 36.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 100,000 | 5 | 33.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 200,000 | 9 | 46.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 200,000 | 5 | 38.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 500,000 | 9 | 51.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 500,000 | 5 | 53.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq09-il | 1,000,000 | 9 | 64.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq09-il | 1,000,000 | 5 | 63.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l7769-il | 50,000 | 9 | 6.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 50,000 | 5 | 15.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l7769-il | 100,000 | 9 | 32.3 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 100,000 | 5 | 39.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l7769-il | 200,000 | 9 | 72.6 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 200,000 | 5 | 74.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l7769-il | 500,000 | 9 | 113.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 500,000 | 5 | 111 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l7769-il | 1,000,000 | 9 | 143.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l7769-il | 1,000,000 | 5 | 136.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188tip-il | 50,000 | 9 | 35.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 50,000 | 5 | 33.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188tip-il | 100,000 | 9 | 55.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 100,000 | 5 | 53.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188tip-il | 200,000 | 9 | 79.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 200,000 | 5 | 72.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188tip-il | 500,000 | 9 | 109 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 500,000 | 5 | 91.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188tip-il | 1,000,000 | 9 | 127 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 1,000,000 | 5 | 93.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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