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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(b707e-il) BOEING 707 .99 SPAN AIRFOIL | Boeing Commercial Airplane Company model 707 airfoils Max thickness 9% at 42% chord Max camber 1.8% at 34% chord | Remove Airfoil details Airfoil plotter |
(ch10sm-il) CH10 (smoothed) | Chuch Hollinger CH 10-48-13 high lift low Reynolds number airfoil Max thickness 12.8% at 30.6% chord Max camber 10.2% at 49.3% chord | Remove Airfoil details Airfoil plotter |
(e1230-il) EPPLER 1230 AIRFOIL | Eppler E1230 general aviation airfoil (Long-EZ and Defiant wing airfoil) Max thickness 17.4% at 30.9% chord Max camber 3.6% at 25.6% chord | Remove Airfoil details Airfoil plotter |
(b737a-il) BOEING 737 ROOT AIRFOIL | Boeing Commercial Airplane Company model 737 airfoils Max thickness 15.4% at 19.6% chord Max camber 0.2% at 5% chord | Remove Airfoil details Airfoil plotter |
(b737b-il) BOEING 737 MIDSPAN AIRFOIL | Boeing Commercial Airplane Company model 737 airfoils Max thickness 12.5% at 29.7% chord Max camber 0.8% at 10% chord | Remove Airfoil details Airfoil plotter |
(s1221-flap-il) S1221 w/ 4 deg flap | Selig S1221 airfoil with 4 deg flap Max thickness 12.1% at 21.8% chord Max camber 5.3% at 52.9% chord | Remove Airfoil details Airfoil plotter |
(m19-il) NACA M19 AIRFOIL | NACA/Munk M-19 airfoil Max thickness 6.2% at 30% chord Max camber 6% at 30% chord | Remove Airfoil details Airfoil plotter |
(vr7b-il) BOEING-VERTOL VR-7 AIRFOIL WITH TAB | Boeing-Vertol VR-7 rotorcraft airfoil with tab Max thickness 12% at 33% chord Max camber 3% at 29% chord | Remove Airfoil details Airfoil plotter |
(oaf095-il) OAF095 AIRFOIL | ONERA/Aerospatiale OAF095 Fenestron airfoil Max thickness 9.5% at 23.2% chord Max camber 3.9% at 53.1% chord | Remove Airfoil details Airfoil plotter |
(e1212-il) EPPLER E1212 AIRFOIL | Eppler E1212 general aviation airfoil Max thickness 17.7% at 23.4% chord Max camber 3.2% at 36.4% chord | Remove Airfoil details Airfoil plotter |
(m13-il) NACA M13 AIRFOIL | NACA/Munk M-13 airfoil Max thickness 6.2% at 30% chord Max camber 3.8% at 30% chord | Remove Airfoil details Airfoil plotter |
(vr5-il) BOEING-VERTOL VR-5 AIRFOIL | Boeing-Vertol VR-5 rotorcraft airfoil Max thickness 12% at 35% chord Max camber 3.4% at 35% chord | Remove Airfoil details Airfoil plotter |
(e1214-il) EPPLER 1214 AIRFOIL | Eppler E1214 general aviation airfoil Max thickness 19.8% at 26.2% chord Max camber 2.1% at 30.4% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (b707e-il,ch10sm-il,e1230-il,b737a-il,b737b-il,s1221-flap-il,m19-il,vr7b-il,oaf095-il,e1212-il,m13-il,vr5-il,e1214-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| b707e-il | 50,000 | 9 | 37 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 50,000 | 5 | 35.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707e-il | 100,000 | 9 | 53.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 100,000 | 5 | 48.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707e-il | 200,000 | 9 | 67.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 200,000 | 5 | 53.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707e-il | 500,000 | 9 | 65.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 500,000 | 5 | 64.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707e-il | 1,000,000 | 9 | 77.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 1,000,000 | 5 | 75.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 50,000 | 9 | 6.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 50,000 | 5 | 12.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 100,000 | 9 | 10.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 100,000 | 5 | 38.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 200,000 | 9 | 73.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 200,000 | 5 | 86.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 500,000 | 9 | 135.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 500,000 | 5 | 132.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ch10sm-il | 1,000,000 | 9 | 175.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ch10sm-il | 1,000,000 | 5 | 164 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 50,000 | 9 | 16.7 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 50,000 | 5 | 24.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 100,000 | 9 | 35.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 100,000 | 5 | 43.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 200,000 | 9 | 56.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 200,000 | 5 | 60.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 500,000 | 9 | 85.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 500,000 | 5 | 86.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1230-il | 1,000,000 | 9 | 111.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1230-il | 1,000,000 | 5 | 104.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737a-il | 50,000 | 9 | 16.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737a-il | 50,000 | 5 | 19.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737a-il | 100,000 | 9 | 23.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737a-il | 100,000 | 5 | 30.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737a-il | 200,000 | 9 | 38.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737a-il | 200,000 | 5 | 46.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737a-il | 500,000 | 9 | 67.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737a-il | 500,000 | 5 | 68.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737a-il | 1,000,000 | 9 | 85.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737a-il | 1,000,000 | 5 | 79.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 50,000 | 9 | 23.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 50,000 | 5 | 26.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 100,000 | 9 | 34.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 100,000 | 5 | 37.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 200,000 | 9 | 47.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 200,000 | 5 | 51 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 500,000 | 9 | 69.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 500,000 | 5 | 71.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 1,000,000 | 9 | 88.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 1,000,000 | 5 | 87.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 50,000 | 9 | 31 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 50,000 | 5 | 39.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 100,000 | 9 | 48.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 100,000 | 5 | 56.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 200,000 | 9 | 69.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 200,000 | 5 | 76.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 500,000 | 9 | 104.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 500,000 | 5 | 106.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1221-flap-il | 1,000,000 | 9 | 133.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1221-flap-il | 1,000,000 | 5 | 129.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 50,000 | 9 | 20.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 50,000 | 5 | 37.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 100,000 | 9 | 57.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 100,000 | 5 | 57.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 200,000 | 9 | 77.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 200,000 | 5 | 75.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 500,000 | 9 | 102.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 500,000 | 5 | 83 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m19-il | 1,000,000 | 9 | 117.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m19-il | 1,000,000 | 5 | 92.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 50,000 | 9 | 30.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 50,000 | 5 | 33.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 100,000 | 9 | 52.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 100,000 | 5 | 53.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 200,000 | 9 | 72.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 200,000 | 5 | 71.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 500,000 | 9 | 99.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 500,000 | 5 | 92.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr7b-il | 1,000,000 | 9 | 118.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr7b-il | 1,000,000 | 5 | 105.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 50,000 | 9 | 43.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 50,000 | 5 | 43.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 100,000 | 9 | 65.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 100,000 | 5 | 63.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 200,000 | 9 | 88.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 200,000 | 5 | 82.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 500,000 | 9 | 116.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 500,000 | 5 | 93.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf095-il | 1,000,000 | 9 | 131.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf095-il | 1,000,000 | 5 | 98.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212-il | 50,000 | 9 | 7.1 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 50,000 | 5 | 23.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212-il | 100,000 | 9 | 32.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 100,000 | 5 | 41.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212-il | 200,000 | 9 | 55.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 200,000 | 5 | 59.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212-il | 500,000 | 9 | 84.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 500,000 | 5 | 85.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1212-il | 1,000,000 | 9 | 109.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1212-il | 1,000,000 | 5 | 107.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m13-il | 50,000 | 9 | 38.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 50,000 | 5 | 40.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m13-il | 100,000 | 9 | 56.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 100,000 | 5 | 56.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m13-il | 200,000 | 9 | 74.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 200,000 | 5 | 73.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m13-il | 500,000 | 9 | 98.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 500,000 | 5 | 95 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m13-il | 1,000,000 | 9 | 115.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m13-il | 1,000,000 | 5 | 86.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr5-il | 50,000 | 9 | 31.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr5-il | 50,000 | 5 | 29.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr5-il | 100,000 | 9 | 55.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr5-il | 100,000 | 5 | 55.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr5-il | 200,000 | 9 | 79.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr5-il | 200,000 | 5 | 78 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr5-il | 500,000 | 9 | 112.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr5-il | 500,000 | 5 | 105.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr5-il | 1,000,000 | 9 | 136.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr5-il | 1,000,000 | 5 | 117.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 50,000 | 9 | 3.1 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 50,000 | 5 | 18.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 100,000 | 9 | 25.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 100,000 | 5 | 36.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 200,000 | 9 | 48.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 200,000 | 5 | 54 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 500,000 | 9 | 78.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 500,000 | 5 | 80.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 1,000,000 | 9 | 105.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 1,000,000 | 5 | 103.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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