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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(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 |
(coanda3-il) Coanda 3 | Coanda 3 airfoil Max thickness 7% at 30% chord Max camber 2.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(marske7-il) RONCZ LOW DRAG FLYING WING AIRFOIL | Roncz/Marske-7 low drag flying wing airfoil Max thickness 12.1% at 42.8% chord Max camber 2.8% at 39.1% chord | Remove Airfoil details Airfoil plotter |
(b737c-il) BOEING 737 MIDSPAN AIRFOIL | Boeing Commercial Airplane Company model 737 airfoils Max thickness 10% at 39.9% chord Max camber 1.5% at 20.4% chord | Remove Airfoil details Airfoil plotter |
(prandtl-d-tip-ns) Prandtl-D tip - NASA Preliminary Research Aerodynamic Design To Lower Drag | NASA Preliminary Research Aerodynamic Design To Lower Drag (PRANDTL-D) glider tip airfoil Max thickness 9.6% at 26.8% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (kc135c-il,coanda3-il,marske7-il,b737c-il,prandtl-d-tip-ns)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| coanda3-il | 50,000 | 9 | 37.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 50,000 | 5 | 37.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda3-il | 100,000 | 9 | 55.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 100,000 | 5 | 52.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda3-il | 200,000 | 9 | 75.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 200,000 | 5 | 67.1 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda3-il | 500,000 | 9 | 94.6 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 500,000 | 5 | 76 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| coanda3-il | 1,000,000 | 9 | 89 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| coanda3-il | 1,000,000 | 5 | 80.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske7-il | 50,000 | 9 | 27.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske7-il | 50,000 | 5 | 24 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske7-il | 100,000 | 9 | 43.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske7-il | 100,000 | 5 | 43.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske7-il | 200,000 | 9 | 72 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske7-il | 200,000 | 5 | 67.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske7-il | 500,000 | 9 | 103.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske7-il | 500,000 | 5 | 90.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske7-il | 1,000,000 | 9 | 120.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske7-il | 1,000,000 | 5 | 96.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737c-il | 50,000 | 9 | 33 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737c-il | 50,000 | 5 | 34.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737c-il | 100,000 | 9 | 49.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737c-il | 100,000 | 5 | 47.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737c-il | 200,000 | 9 | 65.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737c-il | 200,000 | 5 | 58.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737c-il | 500,000 | 9 | 84.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737c-il | 500,000 | 5 | 69.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737c-il | 1,000,000 | 9 | 89.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737c-il | 1,000,000 | 5 | 79.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| prandtl-d-tip-ns | 50,000 | 9 | 25.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-tip-ns | 100,000 | 9 | 35.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-tip-ns | 200,000 | 9 | 47.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-tip-ns | 500,000 | 9 | 62.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-tip-ns | 1,000,000 | 9 | 74.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-tip-ns | 2,000,000 | 9 | 87.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| prandtl-d-tip-ns | 5,000,000 | 9 | 102.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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