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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(lrn1015-il) NASA LRN 1015 (NASA TM 102840) | LRN 1015 airfoil used on the Northrop Grumman RQ-4 Global Hawk airfoil Max thickness 15.2% at 40% chord Max camber 4.9% at 44% chord | Remove Airfoil details Airfoil plotter |
(pt40-il) PT40 | Great Plane PT-40 trainer airfoil Max thickness 11.6% at 27.1% chord Max camber 2.9% at 41.6% 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 |
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Polars for (lrn1015-il,pt40-il,n11-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| lrn1015-il | 50,000 | 9 | 21.9 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 50,000 | 5 | 20.2 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1015-il | 100,000 | 9 | 39.8 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 100,000 | 5 | 34 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1015-il | 200,000 | 9 | 70.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 200,000 | 5 | 72.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1015-il | 500,000 | 9 | 127.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 500,000 | 5 | 112.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lrn1015-il | 1,000,000 | 9 | 154.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lrn1015-il | 1,000,000 | 5 | 134.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 50,000 | 9 | 32.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 50,000 | 5 | 33.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 100,000 | 9 | 48.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 100,000 | 5 | 46.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 200,000 | 9 | 64.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 200,000 | 5 | 57.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 500,000 | 9 | 78.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 500,000 | 5 | 76.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pt40-il | 1,000,000 | 9 | 95 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pt40-il | 1,000,000 | 5 | 89.2 at α=6° | 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 | |
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