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 | ||
(s2027-il) S2027 | Selig S2027 low Reynolds number airfoil Max thickness 14.5% at 29.4% chord Max camber 2.7% at 38.3% chord | Remove Airfoil details Airfoil plotter |
(s1210-il) S1210 12% | Selig S1210 high lift low Reynolds number airfoil Max thickness 12% at 21.4% chord Max camber 6.7% at 51.1% chord | Remove Airfoil details Airfoil plotter |
(kc135c-il) KC-135 BL200.76 AIRFOIL | Boeing KC-135 transonic airfoils Max thickness 10.6% at 40% chord Max camber 1.5% at 25% chord | Remove Airfoil details Airfoil plotter |
(k3-il) GRUMMAN K-3 AIRFOIL | Grumman K-3 transonic airfoil (GAC .70-.83-17.5) Max thickness 17.3% at 33.1% chord Max camber 2.6% at 74.7% chord | Remove Airfoil details Airfoil plotter |
(s2046-il) S2046 | Selig S2046 low Reynolds number airfoil Max thickness 9% at 26.2% chord Max camber 2.6% at 55.1% chord | Remove Airfoil details Airfoil plotter |
(s2048-il) S2048 | Selig S2048 low Reynolds number airfoil Max thickness 8.6% at 35.4% chord Max camber 1.7% at 60.1% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (s2027-il,s1210-il,kc135c-il,k3-il,s2046-il,s2048-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s2027-il | 50,000 | 9 | 8.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2027-il | 50,000 | 5 | 28.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2027-il | 100,000 | 9 | 46 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2027-il | 100,000 | 5 | 50.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2027-il | 200,000 | 9 | 69.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2027-il | 200,000 | 5 | 70.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2027-il | 500,000 | 9 | 99.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2027-il | 500,000 | 5 | 95.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2027-il | 1,000,000 | 9 | 122.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2027-il | 1,000,000 | 5 | 114 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1210-il | 50,000 | 9 | 14.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 50,000 | 5 | 42.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1210-il | 100,000 | 9 | 59.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 100,000 | 5 | 66 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1210-il | 200,000 | 9 | 86.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 200,000 | 5 | 88 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1210-il | 500,000 | 9 | 121.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 500,000 | 5 | 115 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1210-il | 1,000,000 | 9 | 148 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1210-il | 1,000,000 | 5 | 135.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135c-il | 50,000 | 9 | 34.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 50,000 | 5 | 34.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135c-il | 100,000 | 9 | 52 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 100,000 | 5 | 50.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135c-il | 200,000 | 9 | 71.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 200,000 | 5 | 66 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135c-il | 500,000 | 9 | 91.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 500,000 | 5 | 73.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135c-il | 1,000,000 | 9 | 100.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135c-il | 1,000,000 | 5 | 78.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 50,000 | 9 | 24.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 50,000 | 5 | 23 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 100,000 | 9 | 30.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 100,000 | 5 | 33.3 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 200,000 | 9 | 49.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 200,000 | 5 | 50.1 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 500,000 | 9 | 79.4 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 500,000 | 5 | 65.9 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3-il | 1,000,000 | 9 | 94.2 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3-il | 1,000,000 | 5 | 70.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2046-il | 50,000 | 9 | 38.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 50,000 | 5 | 40.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2046-il | 100,000 | 9 | 58 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 100,000 | 5 | 55.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2046-il | 200,000 | 9 | 77.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 200,000 | 5 | 70.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2046-il | 500,000 | 9 | 101.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 500,000 | 5 | 84.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2046-il | 1,000,000 | 9 | 108.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2046-il | 1,000,000 | 5 | 93.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2048-il | 50,000 | 9 | 37.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2048-il | 50,000 | 5 | 37.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2048-il | 100,000 | 9 | 55.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2048-il | 100,000 | 5 | 52.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2048-il | 200,000 | 9 | 75.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2048-il | 200,000 | 5 | 67.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2048-il | 500,000 | 9 | 100.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2048-il | 500,000 | 5 | 78.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2048-il | 1,000,000 | 9 | 110.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2048-il | 1,000,000 | 5 | 88.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||