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 | ||
(hq308-il) HQ 3.0/8 AIRFOIL | Quabeck HQ 3.0/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 3% at 50% chord | Remove Airfoil details Airfoil plotter |
(isa961-il) I.S.A. 961 | I.S.A. 961 airfoil Max thickness 9.3% at 20% chord Max camber 4.6% at 40% 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 |
(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 |
(a63a108c-il) NASA/AMES 63A108 MOD C AIRFOIL | NASA/AMES modification of the NACA 63A-108 airfoil Max thickness 7.7% at 30% chord Max camber 0.5% at 12.5% chord | Remove Airfoil details Airfoil plotter |
(kc135a-il) KC-135 BL52.44 AIRFOIL | Boeing KC-135 transonic airfoils Max thickness 15.5% at 35% chord Max camber 1.3% at 20% chord | Remove Airfoil details Airfoil plotter |
(la203a-il) DOUGLAS LA203A AIRFOIL | Douglas/Liebeck LA203A high lift airfoil Max thickness 15.7% at 34.3% chord Max camber 5.5% at 46% chord | Remove Airfoil details Airfoil plotter |
(k3311-il) K3311 (original) | Leon Kincaid K3311 airfoil (original) Max thickness 11% at 30% chord Max camber 3.3% at 40% chord | Remove Airfoil details Airfoil plotter |
(kc135b-il) KC-135 BL124.32 AIRFOIL | Boeing KC-135 transonic airfoils Max thickness 13% at 40% chord Max camber 1.4% at 20% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (hq308-il,isa961-il,l7769-il,kc135c-il,a63a108c-il,kc135a-il,la203a-il,k3311-il,kc135b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hq308-il | 50,000 | 9 | 40.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 50,000 | 5 | 42.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq308-il | 100,000 | 9 | 62.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 100,000 | 5 | 60.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq308-il | 200,000 | 9 | 86.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 200,000 | 5 | 79.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq308-il | 500,000 | 9 | 116.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 500,000 | 5 | 99.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq308-il | 1,000,000 | 9 | 135.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq308-il | 1,000,000 | 5 | 99.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa961-il | 50,000 | 9 | 34.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa961-il | 50,000 | 5 | 39.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa961-il | 100,000 | 9 | 55.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa961-il | 100,000 | 5 | 53.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa961-il | 200,000 | 9 | 70.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa961-il | 200,000 | 5 | 63 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa961-il | 500,000 | 9 | 80 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa961-il | 500,000 | 5 | 75.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| isa961-il | 1,000,000 | 9 | 90.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| isa961-il | 1,000,000 | 5 | 88.9 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 | |
| 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 | |
| a63a108c-il | 50,000 | 9 | 24.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a63a108c-il | 50,000 | 5 | 22.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a63a108c-il | 100,000 | 9 | 31.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a63a108c-il | 100,000 | 5 | 31.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a63a108c-il | 200,000 | 9 | 37.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a63a108c-il | 200,000 | 5 | 41.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a63a108c-il | 500,000 | 9 | 54.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a63a108c-il | 500,000 | 5 | 58.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a63a108c-il | 1,000,000 | 9 | 69.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a63a108c-il | 1,000,000 | 5 | 72.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135a-il | 50,000 | 9 | 24.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 50,000 | 5 | 27.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135a-il | 100,000 | 9 | 47.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 100,000 | 5 | 47.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135a-il | 200,000 | 9 | 68.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 200,000 | 5 | 62.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135a-il | 500,000 | 9 | 88.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 500,000 | 5 | 73.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135a-il | 1,000,000 | 9 | 97.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135a-il | 1,000,000 | 5 | 82.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 50,000 | 9 | 6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 50,000 | 5 | 13.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 100,000 | 9 | 30.6 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 100,000 | 5 | 46.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 200,000 | 9 | 82.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 200,000 | 5 | 85.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 500,000 | 9 | 127.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 500,000 | 5 | 124 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la203a-il | 1,000,000 | 9 | 160.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la203a-il | 1,000,000 | 5 | 151.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311-il | 50,000 | 9 | 34.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 50,000 | 5 | 36.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311-il | 100,000 | 9 | 55.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 100,000 | 5 | 56.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311-il | 200,000 | 9 | 77.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 200,000 | 5 | 76.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311-il | 500,000 | 9 | 107.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 500,000 | 5 | 100.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311-il | 1,000,000 | 9 | 129.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311-il | 1,000,000 | 5 | 116.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135b-il | 50,000 | 9 | 31.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 50,000 | 5 | 31.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135b-il | 100,000 | 9 | 50.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 100,000 | 5 | 49.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135b-il | 200,000 | 9 | 70.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 200,000 | 5 | 62.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135b-il | 500,000 | 9 | 89.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 500,000 | 5 | 71.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135b-il | 1,000,000 | 9 | 98.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135b-il | 1,000,000 | 5 | 79.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||