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 | ||
(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 |
(ls413mod-il) NASA/LANGLEY LS(1)-0413MOD AIRFOIL | NASA/Langley LS(1)-0413MOD general aviation airfoil Max thickness 13% at 35% chord Max camber 2.2% at 40% chord | Remove Airfoil details Airfoil plotter |
(pw98mod-pw) PW98-mod | Peter Wick. Modified PW51 with higher camber and therefore a higher clmax Max thickness 8.4% at 27.5% chord Max camber 1.8% at 27.5% chord | Remove Airfoil details Airfoil plotter |
(hq1010-il) HQ 1.0/10 AIRFOIL | Quabeck HQ 1.0/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 1% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (prandtl-d-tip-ns,ls413mod-il,pw98mod-pw,hq1010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| ls413mod-il | 50,000 | 9 | 34.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413mod-il | 50,000 | 5 | 35.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413mod-il | 100,000 | 9 | 53.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413mod-il | 100,000 | 5 | 49.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413mod-il | 200,000 | 9 | 66 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413mod-il | 200,000 | 5 | 62 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413mod-il | 500,000 | 9 | 86.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413mod-il | 500,000 | 5 | 77.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls413mod-il | 1,000,000 | 9 | 99.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls413mod-il | 1,000,000 | 5 | 92.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pw98mod-pw | 50,000 | 9 | 26.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw98mod-pw | 100,000 | 9 | 45.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw98mod-pw | 200,000 | 9 | 59 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw98mod-pw | 500,000 | 9 | 71.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw98mod-pw | 1,000,000 | 9 | 81.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw98mod-pw | 2,000,000 | 9 | 90.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw98mod-pw | 5,000,000 | 9 | 106.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 50,000 | 9 | 32.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 50,000 | 5 | 32.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 100,000 | 9 | 47.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 100,000 | 5 | 45.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 200,000 | 9 | 63.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 200,000 | 5 | 55.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 500,000 | 9 | 79.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 500,000 | 5 | 68.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq1010-il | 1,000,000 | 9 | 85.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq1010-il | 1,000,000 | 5 | 78 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||