Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(s1223rtl-il) S1223 RTL | Richard T. LaSalle modification of the S1223 to S1223RTL Max thickness 13.5% at 19.9% chord Max camber 8.3% at 55.2% chord | Remove Airfoil details Airfoil plotter |
(c5c-il) LOCKHEED C-5A BL576 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord Max camber 1.4% at 65% 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 |
(davis-corrected-il) DAVIS BASIC B-24 WING AIRFOIL | Davis basic B-24 wing airfoil Max thickness 15.9% at 29.6% chord Max camber 2.5% at 29.6% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (s1223rtl-il,c5c-il,l7769-il,davis-corrected-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s1223rtl-il | 50,000 | 9 | 31.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 50,000 | 5 | 35.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223rtl-il | 100,000 | 9 | 43.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 100,000 | 5 | 49.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223rtl-il | 200,000 | 9 | 98 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 200,000 | 5 | 64.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223rtl-il | 500,000 | 9 | 84 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 500,000 | 5 | 85.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1223rtl-il | 1,000,000 | 9 | 106.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1223rtl-il | 1,000,000 | 5 | 106.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 50,000 | 9 | 31.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 50,000 | 5 | 30.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 100,000 | 9 | 48.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 100,000 | 5 | 44.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 200,000 | 9 | 67.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 200,000 | 5 | 55.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 500,000 | 9 | 78.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 500,000 | 5 | 62.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5c-il | 1,000,000 | 9 | 82.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5c-il | 1,000,000 | 5 | 77.6 at α=9° | 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 | |
| davis-corrected-il | 50,000 | 9 | 12.5 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 100,000 | 9 | 36.4 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 200,000 | 9 | 63.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 500,000 | 9 | 96.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 1,000,000 | 9 | 122.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 2,000,000 | 9 | 137.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-corrected-il | 5,000,000 | 9 | 157.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||