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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(s2055-il) S2055 | Selig S2055 low Reynolds number airfoil Max thickness 8% at 34.8% chord Max camber 1.4% at 44.6% chord | Remove Airfoil details Airfoil plotter |
(m17-il) NACA M17 AIRFOIL | NACA/Munk M-17 airfoil Max thickness 8.1% at 40% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
(davis-il) Davis AIRFOIL | Consolidated/Davis airfoil (B-24 wing?) Max thickness 11.3% at 30% chord Max camber 3.7% at 40% chord | Remove Airfoil details Airfoil plotter |
(c5b-il) LOCKHEED C-5A BL488.2 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.5% at 40% chord Max camber 1.2% at 70% chord | Remove Airfoil details Airfoil plotter |
(ht08-il) HT08 | Drela HT08 airfoil Max thickness 5% at 20.2% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(lds2-il) LDS-2 AIRFOIL | LDS-2 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 45% chord | Remove Airfoil details Airfoil plotter |
(davissm-il) davissm | Davis 3R F1B free flight airfoil (smoothed) Max thickness 5.9% at 30.6% chord Max camber 5.9% at 45.4% chord | Remove Airfoil details Airfoil plotter |
(dga1182-il) D.G.A. 1182 | D.G.A. 1182 airfoil Max thickness 7.6% at 30% chord Max camber 0.9% at 20% chord | Remove Airfoil details Airfoil plotter |
(l188tip-il) LOCKHEED L-188 TIP AIRFOIL | Lockheed L-188/P-3 tip airfoil NACA 0012 -1.10 40/1.051 Cli=.4 a=.8 Max thickness 12% at 41.3% chord Max camber 2.7% at 51.7% chord | Remove Airfoil details Airfoil plotter |
(s2050-il) S2050 8.93% | Selig S2050 low Reynolds number airfoil Max thickness 8.9% at 29.8% chord Max camber 1.1% at 69.5% chord | Remove Airfoil details Airfoil plotter |
(s2027-il) S2027 | Selig S2027 low Reynolds number airfoil Max thickness 14.5% at 29.4% chord Max camber 2.7% at 38.3% chord | Remove Airfoil details Airfoil plotter |
(ht05-il) HT05 | Drela HT05 airfoil Max thickness 4.8% at 17.1% chord Max camber 0% at 63.3% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (s2055-il,m17-il,davis-il,c5b-il,ht08-il,lds2-il,davissm-il,dga1182-il,l188tip-il,s2050-il,s2027-il,ht05-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s2055-il | 50,000 | 9 | 35.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 50,000 | 5 | 35.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 100,000 | 9 | 51.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 100,000 | 5 | 48.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 200,000 | 9 | 70.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 200,000 | 5 | 61.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 500,000 | 9 | 92.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 500,000 | 5 | 71.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 1,000,000 | 9 | 95.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 1,000,000 | 5 | 81 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 50,000 | 9 | 35.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 50,000 | 5 | 35.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 100,000 | 9 | 55.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 100,000 | 5 | 55.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 200,000 | 9 | 75.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 200,000 | 5 | 74.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 500,000 | 9 | 102.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 500,000 | 5 | 98.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 1,000,000 | 9 | 122.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 1,000,000 | 5 | 114.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-il | 50,000 | 9 | 22.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 50,000 | 5 | 36.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-il | 100,000 | 9 | 54 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 100,000 | 5 | 55 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-il | 200,000 | 9 | 76.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 200,000 | 5 | 72.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-il | 500,000 | 9 | 101.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 500,000 | 5 | 91.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davis-il | 1,000,000 | 9 | 120.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davis-il | 1,000,000 | 5 | 107 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5b-il | 50,000 | 9 | 30.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 50,000 | 5 | 29.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5b-il | 100,000 | 9 | 46.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 100,000 | 5 | 42.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5b-il | 200,000 | 9 | 64.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 200,000 | 5 | 50.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5b-il | 500,000 | 9 | 73.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 500,000 | 5 | 61.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5b-il | 1,000,000 | 9 | 78.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5b-il | 1,000,000 | 5 | 77.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht08-il | 50,000 | 9 | 21.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht08-il | 50,000 | 5 | 20.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht08-il | 100,000 | 9 | 28.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht08-il | 100,000 | 5 | 26.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht08-il | 200,000 | 9 | 33.1 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht08-il | 200,000 | 5 | 34.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht08-il | 500,000 | 9 | 44.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht08-il | 500,000 | 5 | 48.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht08-il | 1,000,000 | 9 | 56.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht08-il | 1,000,000 | 5 | 63.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lds2-il | 50,000 | 9 | 34 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lds2-il | 50,000 | 5 | 33.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lds2-il | 100,000 | 9 | 52.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lds2-il | 100,000 | 5 | 50.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lds2-il | 200,000 | 9 | 72.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lds2-il | 200,000 | 5 | 66.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lds2-il | 500,000 | 9 | 97.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lds2-il | 500,000 | 5 | 77.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| lds2-il | 1,000,000 | 9 | 106.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| lds2-il | 1,000,000 | 5 | 85.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davissm-il | 50,000 | 9 | 45.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 50,000 | 5 | 45.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davissm-il | 100,000 | 9 | 70.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 100,000 | 5 | 69.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davissm-il | 200,000 | 9 | 96.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 200,000 | 5 | 92.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davissm-il | 500,000 | 9 | 131.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 500,000 | 5 | 118.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| davissm-il | 1,000,000 | 9 | 154.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| davissm-il | 1,000,000 | 5 | 128.8 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1182-il | 50,000 | 9 | 22.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 50,000 | 5 | 20.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1182-il | 100,000 | 9 | 24.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 100,000 | 5 | 27.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1182-il | 200,000 | 9 | 29.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 200,000 | 5 | 37.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1182-il | 500,000 | 9 | 41.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 500,000 | 5 | 47.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dga1182-il | 1,000,000 | 9 | 57.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dga1182-il | 1,000,000 | 5 | 55.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188tip-il | 50,000 | 9 | 35.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 50,000 | 5 | 33.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188tip-il | 100,000 | 9 | 55.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 100,000 | 5 | 53.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188tip-il | 200,000 | 9 | 79.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 200,000 | 5 | 72.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188tip-il | 500,000 | 9 | 109 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 500,000 | 5 | 91.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| l188tip-il | 1,000,000 | 9 | 127 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| l188tip-il | 1,000,000 | 5 | 93.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2050-il | 50,000 | 9 | 33.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2050-il | 50,000 | 5 | 34.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2050-il | 100,000 | 9 | 48.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2050-il | 100,000 | 5 | 47 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2050-il | 200,000 | 9 | 63.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2050-il | 200,000 | 5 | 58.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2050-il | 500,000 | 9 | 80.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2050-il | 500,000 | 5 | 70.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2050-il | 1,000,000 | 9 | 88.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2050-il | 1,000,000 | 5 | 80.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2027-il | 50,000 | 9 | 8.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2027-il | 50,000 | 5 | 28.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2027-il | 100,000 | 9 | 46 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2027-il | 100,000 | 5 | 50.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2027-il | 200,000 | 9 | 69.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2027-il | 200,000 | 5 | 70.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2027-il | 500,000 | 9 | 99.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2027-il | 500,000 | 5 | 95.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2027-il | 1,000,000 | 9 | 122.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2027-il | 1,000,000 | 5 | 114 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 50,000 | 9 | 19.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 50,000 | 5 | 19.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 100,000 | 9 | 24.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 100,000 | 5 | 26.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 200,000 | 9 | 31.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 200,000 | 5 | 34.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 500,000 | 9 | 44.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 500,000 | 5 | 49.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht05-il | 1,000,000 | 9 | 57.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht05-il | 1,000,000 | 5 | 63.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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