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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(dsma523b-il) DSMA-523B AIRFOIL | McDonnell/Douglas DSMA-523 transonic airfoil with blunt trailing edge Max thickness 11% at 36% chord Max camber 2.4% at 82% chord | Remove Airfoil details Airfoil plotter |
(npl9626-il) NPL 9626 AIRFOIL | NPL 9626 rotorcraft airfoil Max thickness 12.1% at 30.9% chord Max camber 0.7% at 30.9% chord | Remove Airfoil details Airfoil plotter |
(hq300gd2-il) HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL | DFVLR/Braunschweig Horstmann and Quast HQ-300 GD(MOD 2) sailplane airfoil Max thickness 16.6% at 39.1% chord Max camber 3.9% at 39.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (dsma523b-il,npl9626-il,hq300gd2-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
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dsma523b-il | 50,000 | 9 | 20.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
dsma523b-il | 50,000 | 5 | 20.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
dsma523b-il | 100,000 | 9 | 23.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
dsma523b-il | 100,000 | 5 | 27.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
dsma523b-il | 200,000 | 9 | 29.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
dsma523b-il | 200,000 | 5 | 39.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
dsma523b-il | 500,000 | 9 | 49.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
dsma523b-il | 500,000 | 5 | 60 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
dsma523b-il | 1,000,000 | 9 | 73.2 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
dsma523b-il | 1,000,000 | 5 | 77.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
npl9626-il | 50,000 | 9 | 29.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
npl9626-il | 50,000 | 5 | 29.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
npl9626-il | 100,000 | 9 | 42.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
npl9626-il | 100,000 | 5 | 39.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
npl9626-il | 200,000 | 9 | 53.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
npl9626-il | 200,000 | 5 | 48.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
npl9626-il | 500,000 | 9 | 65.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
npl9626-il | 500,000 | 5 | 60.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
npl9626-il | 1,000,000 | 9 | 73.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
npl9626-il | 1,000,000 | 5 | 76.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
hq300gd2-il | 50,000 | 9 | 5.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
hq300gd2-il | 50,000 | 5 | 15.1 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
hq300gd2-il | 100,000 | 9 | 42.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
hq300gd2-il | 100,000 | 5 | 44.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
hq300gd2-il | 200,000 | 9 | 74.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
hq300gd2-il | 200,000 | 5 | 73.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
hq300gd2-il | 500,000 | 9 | 107.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
hq300gd2-il | 500,000 | 5 | 107.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
hq300gd2-il | 1,000,000 | 9 | 139.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
hq300gd2-il | 1,000,000 | 5 | 131.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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