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 | ||
(s1091-il) S1091 | Selig S1091 airfoil Max thickness 5.1% at 13.4% chord Max camber 5.7% at 45.1% chord | Remove Airfoil details Airfoil plotter |
(s1016-il) S1016 | Selig S1016 HPV airfoil Max thickness 17.5% at 41.8% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(bacnlf-il) BOEING HSNLF AIRFOIL | Boeing high speed natural laminar flow airfoil from a European patent (EP 0111785A1) Max thickness 10.1% at 43.7% chord Max camber 1.3% at 76.7% chord | Remove Airfoil details Airfoil plotter |
(n11-il) N-11 | N-11 airfoil Max thickness 10.9% at 30% chord Max camber 4.4% at 40% chord | Remove Airfoil details Airfoil plotter |
(giiij-il) GIII BL332 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35% chord Max camber 1.4% at 25% chord | Remove Airfoil details Airfoil plotter |
(kc135d-il) KC-135 BL351.6 AIRFOIL | Boeing KC-135 transonic airfoils Max thickness 9% at 40% chord Max camber 1.9% at 30% chord | Remove Airfoil details Airfoil plotter |
(usa27-il) USA 27 AIRFOIL | USA-27 airfoil Max thickness 11.1% at 30% chord Max camber 5.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(giiil-il) GIII BL387 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35.1% chord Max camber 1.6% at 25.1% chord | Remove Airfoil details Airfoil plotter |
(e171-il) (Dicke 12.28%) | Eppler E171 low Reynolds number airfoil Max thickness 12.3% at 32.4% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(rae101-il) RAE 101 AIRFOIL | RAE 101 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(oaf139-il) OAF139 AIRFOIL | ONERA/Aerospatiale OAF139 Fenestron airfoil Max thickness 13.7% at 23.2% chord Max camber 0% at 0.1% chord | Remove Airfoil details Airfoil plotter |
(th25816-il) TH 25816 HALE AIRFOIL | Naval Air Development Center/Doug Hall high altitude Max thickness 25.7% at 48.3% chord Max camber 4% at 52.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (s1091-il,s1016-il,bacnlf-il,n11-il,giiij-il,kc135d-il,usa27-il,giiil-il,e171-il,rae101-il,oaf139-il,th25816-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s1091-il | 50,000 | 9 | 46.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 50,000 | 5 | 48.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1091-il | 100,000 | 9 | 70.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 100,000 | 5 | 69.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1091-il | 200,000 | 9 | 96.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 200,000 | 5 | 90.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1091-il | 500,000 | 9 | 129.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 500,000 | 5 | 111 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1091-il | 1,000,000 | 9 | 153 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 1,000,000 | 5 | 117.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 50,000 | 9 | 28.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 50,000 | 5 | 22.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 100,000 | 9 | 39.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 100,000 | 5 | 23.5 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 200,000 | 9 | 35.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 200,000 | 5 | 30.2 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 500,000 | 9 | 40.1 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 500,000 | 5 | 41.8 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 1,000,000 | 9 | 52.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 1,000,000 | 5 | 52 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 50,000 | 9 | 26.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 50,000 | 5 | 28.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 100,000 | 9 | 35.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 100,000 | 5 | 40.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 200,000 | 9 | 55.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 200,000 | 5 | 53 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 500,000 | 9 | 78.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 500,000 | 5 | 64.9 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacnlf-il | 1,000,000 | 9 | 88.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacnlf-il | 1,000,000 | 5 | 66.1 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n11-il | 50,000 | 9 | 27.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11-il | 50,000 | 5 | 38.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n11-il | 100,000 | 9 | 54.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11-il | 100,000 | 5 | 56.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n11-il | 200,000 | 9 | 75.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11-il | 200,000 | 5 | 72 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n11-il | 500,000 | 9 | 100.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11-il | 500,000 | 5 | 93.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n11-il | 1,000,000 | 9 | 118.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n11-il | 1,000,000 | 5 | 111.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiij-il | 50,000 | 9 | 32.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 50,000 | 5 | 32.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiij-il | 100,000 | 9 | 46.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 100,000 | 5 | 43.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiij-il | 200,000 | 9 | 59.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 200,000 | 5 | 52.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiij-il | 500,000 | 9 | 73.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 500,000 | 5 | 65.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiij-il | 1,000,000 | 9 | 79.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiij-il | 1,000,000 | 5 | 79.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 50,000 | 9 | 36.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 50,000 | 5 | 36.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 100,000 | 9 | 54.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 100,000 | 5 | 52.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 200,000 | 9 | 74.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 200,000 | 5 | 68.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 500,000 | 9 | 100.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 500,000 | 5 | 84 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135d-il | 1,000,000 | 9 | 114.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135d-il | 1,000,000 | 5 | 86.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 50,000 | 9 | 20.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 50,000 | 5 | 35.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 100,000 | 9 | 50.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 100,000 | 5 | 52.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 200,000 | 9 | 69.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 200,000 | 5 | 69 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 500,000 | 9 | 95.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 500,000 | 5 | 92 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 1,000,000 | 9 | 117.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 1,000,000 | 5 | 110.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 50,000 | 9 | 31.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 50,000 | 5 | 31.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 100,000 | 9 | 45 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 100,000 | 5 | 42.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 200,000 | 9 | 57.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 200,000 | 5 | 51.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 500,000 | 9 | 72.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 500,000 | 5 | 67.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiil-il | 1,000,000 | 9 | 82 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiil-il | 1,000,000 | 5 | 82.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e171-il | 50,000 | 9 | 29.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 50,000 | 5 | 29.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e171-il | 100,000 | 9 | 43.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 100,000 | 5 | 41.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e171-il | 200,000 | 9 | 56.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 200,000 | 5 | 47.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e171-il | 500,000 | 9 | 65.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 500,000 | 5 | 56.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e171-il | 1,000,000 | 9 | 68.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e171-il | 1,000,000 | 5 | 68.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae101-il | 50,000 | 9 | 27.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 50,000 | 5 | 27.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae101-il | 100,000 | 9 | 39 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 100,000 | 5 | 36.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae101-il | 200,000 | 9 | 49.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 200,000 | 5 | 44.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae101-il | 500,000 | 9 | 60.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 500,000 | 5 | 56.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rae101-il | 1,000,000 | 9 | 67.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rae101-il | 1,000,000 | 5 | 70.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf139-il | 50,000 | 9 | 13.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf139-il | 50,000 | 5 | 20.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf139-il | 100,000 | 9 | 26.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf139-il | 100,000 | 5 | 31.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf139-il | 200,000 | 9 | 39.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf139-il | 200,000 | 5 | 43.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf139-il | 500,000 | 9 | 58.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf139-il | 500,000 | 5 | 59.8 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| oaf139-il | 1,000,000 | 9 | 73.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| oaf139-il | 1,000,000 | 5 | 72.3 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 50,000 | 9 | 2.4 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 50,000 | 5 | 7.1 at α=19° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 100,000 | 9 | 15.1 at α=17.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 100,000 | 5 | 12.2 at α=16° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 200,000 | 9 | 21.5 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 200,000 | 5 | 19.1 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 500,000 | 9 | 54.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 500,000 | 5 | 47.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| th25816-il | 1,000,000 | 9 | 74.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| th25816-il | 1,000,000 | 5 | 59.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||