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 | ||
(raf89-il) RAF 89 AIRFOIL | RAF-89 airfoil Max thickness 25% at 30% chord Max camber 1.6% at 50% chord | Remove Airfoil details Airfoil plotter |
(rhodesg30-il) Rhode St. Genese 30 | Rhode St. Genese 30 airfoil Max thickness 9.7% at 30% chord Max camber 3.2% at 40% chord | Remove Airfoil details Airfoil plotter |
(raf31-il) RAF 31 AIRFOIL | RAF-31 airfoil Max thickness 12.7% at 30% chord Max camber 2.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(raf34-il) RAF 34 AIRFOIL | RAF-34 airfoil Max thickness 12.6% at 30% chord Max camber 2% at 30% chord | Remove Airfoil details Airfoil plotter |
(rg14-il) RG 14 AIRFOIL | Rolf Girsberger RG 14 airfoil Max thickness 8.5% at 29.7% chord Max camber 1.6% at 39.2% chord | Remove Airfoil details Airfoil plotter |
(raf33-il) RAF 33 AIRFOIL | RAF-33 airfoil Max thickness 12.6% at 30% chord Max camber 4.7% at 30% chord | Remove Airfoil details Airfoil plotter |
(raf30-il) RAF 30 AIRFOIL | RAF-30 airfoil Max thickness 12.6% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(raf28-il) RAF 28 AIRFOIL | RAF-28 airfoil Max thickness 9.8% at 30% chord Max camber 1.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(rc12n1-il) NASA/LANGLEY RC-12(N)1 AIRFOIL | NASA/Langley RC-12(N)1 rotorcraft airfoil Max thickness 12% at 37.4% chord Max camber 1.4% at 30% chord | Remove Airfoil details Airfoil plotter |
(raf48-il) RAF-48 AIRFOIL | RAF-48 airfoil Max thickness 15% at 30% chord Max camber 2.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(raf27-il) RAF 27 AIRFOIL | RAF-27 airfoil Max thickness 9.8% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(raf6-il) RAF 6 AIRFOIL | RAF-6 airfoil Max thickness 10% at 30% chord Max camber 4.6% at 30% chord | Remove Airfoil details Airfoil plotter |
(raf38-il) RAF 38 AIRFOIL | RAF-38 airfoil Max thickness 12.7% at 30% chord Max camber 2.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(rc08n1-il) NASA/LANGLEY RC-08(N)1 AIRFOIL | NASA/Langley RC-08(N)1 rotorcraft airfoil Max thickness 8% at 37.5% chord Max camber 1.6% at 25% chord | Remove Airfoil details Airfoil plotter |
(rg15-il) RG-15 8.9% | Rolf Girsberger RG 15 low Reynolds number airfoil Max thickness 8.9% at 30.2% chord Max camber 1.8% at 39.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (raf89-il,rhodesg30-il,raf31-il,raf34-il,rg14-il,raf33-il,raf30-il,raf28-il,rc12n1-il,raf48-il,raf27-il,raf6-il,raf38-il,rc08n1-il,rg15-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| raf89-il | 50,000 | 9 | 1.6 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 50,000 | 5 | 7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 100,000 | 9 | 18.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 100,000 | 5 | 27.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 200,000 | 9 | 45.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 200,000 | 5 | 36 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 500,000 | 9 | 50.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 500,000 | 5 | 39.7 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf89-il | 1,000,000 | 9 | 56.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf89-il | 1,000,000 | 5 | 45.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg30-il | 50,000 | 9 | 34.7 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg30-il | 50,000 | 5 | 36.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg30-il | 100,000 | 9 | 51.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg30-il | 100,000 | 5 | 51.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg30-il | 200,000 | 9 | 67.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg30-il | 200,000 | 5 | 66.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg30-il | 500,000 | 9 | 88.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg30-il | 500,000 | 5 | 84.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg30-il | 1,000,000 | 9 | 105.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg30-il | 1,000,000 | 5 | 85.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf31-il | 50,000 | 9 | 33.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf31-il | 50,000 | 5 | 33.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf31-il | 100,000 | 9 | 53 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf31-il | 100,000 | 5 | 50.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf31-il | 200,000 | 9 | 72.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf31-il | 200,000 | 5 | 65 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf31-il | 500,000 | 9 | 93.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf31-il | 500,000 | 5 | 79.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf31-il | 1,000,000 | 9 | 106.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf31-il | 1,000,000 | 5 | 83.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf34-il | 50,000 | 9 | 25.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 50,000 | 5 | 30.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf34-il | 100,000 | 9 | 48.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 100,000 | 5 | 49.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf34-il | 200,000 | 9 | 67.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 200,000 | 5 | 65.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf34-il | 500,000 | 9 | 90.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 500,000 | 5 | 79.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf34-il | 1,000,000 | 9 | 99.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf34-il | 1,000,000 | 5 | 84.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14-il | 50,000 | 9 | 33.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14-il | 50,000 | 5 | 34.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14-il | 100,000 | 9 | 49.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14-il | 100,000 | 5 | 47.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14-il | 200,000 | 9 | 64.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14-il | 200,000 | 5 | 59.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14-il | 500,000 | 9 | 83.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14-il | 500,000 | 5 | 74 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg14-il | 1,000,000 | 9 | 95.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg14-il | 1,000,000 | 5 | 84.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf33-il | 50,000 | 9 | 6.6 at α=-5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf33-il | 50,000 | 5 | 19.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf33-il | 100,000 | 9 | 39 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf33-il | 100,000 | 5 | 48.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf33-il | 200,000 | 9 | 71.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf33-il | 200,000 | 5 | 73.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf33-il | 500,000 | 9 | 107.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf33-il | 500,000 | 5 | 99.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf33-il | 1,000,000 | 9 | 127.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf33-il | 1,000,000 | 5 | 110.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 50,000 | 9 | 28.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 50,000 | 5 | 28.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 100,000 | 9 | 41.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 100,000 | 5 | 39.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 200,000 | 9 | 52.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 200,000 | 5 | 45.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 500,000 | 9 | 58.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 500,000 | 5 | 58.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf30-il | 1,000,000 | 9 | 69.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf30-il | 1,000,000 | 5 | 71.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 50,000 | 9 | 35.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 50,000 | 5 | 35.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 100,000 | 9 | 52.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 100,000 | 5 | 50.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 200,000 | 9 | 69.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 200,000 | 5 | 64.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 500,000 | 9 | 90.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 500,000 | 5 | 79.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf28-il | 1,000,000 | 9 | 103.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf28-il | 1,000,000 | 5 | 83.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 50,000 | 9 | 32 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 50,000 | 5 | 31.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 100,000 | 9 | 49.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 100,000 | 5 | 47.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 200,000 | 9 | 66.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 200,000 | 5 | 61 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 500,000 | 9 | 86.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 500,000 | 5 | 70.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc12n1-il | 1,000,000 | 9 | 92.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc12n1-il | 1,000,000 | 5 | 76.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 50,000 | 9 | 7.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 50,000 | 5 | 25.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 100,000 | 9 | 45.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 100,000 | 5 | 49.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 200,000 | 9 | 68.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 200,000 | 5 | 67.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 500,000 | 9 | 97.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 500,000 | 5 | 93.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf48-il | 1,000,000 | 9 | 121.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf48-il | 1,000,000 | 5 | 108.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf27-il | 50,000 | 9 | 28.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 50,000 | 5 | 27.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf27-il | 100,000 | 9 | 39.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 100,000 | 5 | 36.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf27-il | 200,000 | 9 | 49.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 200,000 | 5 | 43.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf27-il | 500,000 | 9 | 56.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 500,000 | 5 | 58.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf27-il | 1,000,000 | 9 | 69.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf27-il | 1,000,000 | 5 | 71.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf6-il | 50,000 | 9 | 35.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf6-il | 50,000 | 5 | 36.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf6-il | 100,000 | 9 | 51.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf6-il | 100,000 | 5 | 52.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf6-il | 200,000 | 9 | 70.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf6-il | 200,000 | 5 | 68.2 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf6-il | 500,000 | 9 | 90.5 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf6-il | 500,000 | 5 | 85 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf6-il | 1,000,000 | 9 | 104.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf6-il | 1,000,000 | 5 | 105 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf38-il | 50,000 | 9 | 31.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 50,000 | 5 | 32.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf38-il | 100,000 | 9 | 51.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 100,000 | 5 | 51.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf38-il | 200,000 | 9 | 71.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 200,000 | 5 | 69 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf38-il | 500,000 | 9 | 96.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 500,000 | 5 | 90.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf38-il | 1,000,000 | 9 | 114.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf38-il | 1,000,000 | 5 | 98.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08n1-il | 50,000 | 9 | 33.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 50,000 | 5 | 33.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08n1-il | 100,000 | 9 | 48.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 100,000 | 5 | 45.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08n1-il | 200,000 | 9 | 63.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 200,000 | 5 | 56.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08n1-il | 500,000 | 9 | 81.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 500,000 | 5 | 67.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc08n1-il | 1,000,000 | 9 | 91.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc08n1-il | 1,000,000 | 5 | 76.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15-il | 50,000 | 9 | 34.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 50,000 | 5 | 36.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15-il | 100,000 | 9 | 52.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 100,000 | 5 | 50.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15-il | 200,000 | 9 | 68.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 200,000 | 5 | 63.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15-il | 500,000 | 9 | 89 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 500,000 | 5 | 79 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rg15-il | 1,000,000 | 9 | 102.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rg15-il | 1,000,000 | 5 | 88.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||