SPICA 11.73% smoothed (spicasm-il)
SPICA 11.73% smoothed - Anderson SPICA R/C sailplane airfoil (smoothed)
| Details | Dat file | Parser | |
|
(spicasm-il) SPICA 11.73% smoothed Anderson SPICA R/C sailplane airfoil (smoothed) Max thickness 11.7% at 30% chord. Max camber 4.7% at 35% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
SPICA 11.73% smoothed 1.00000 0.0 0.95000 0.01195 0.90000 0.02270 0.85000 0.03275 0.80000 0.04260 0.75000 0.05238 0.70000 0.06190 0.65000 0.07107 0.60000 0.07970 0.55000 0.08773 0.50000 0.09490 0.45000 0.10053 0.40000 0.10415 0.35000 0.10583 0.30000 0.10530 0.25000 0.10242 0.20000 0.09690 0.15000 0.08805 0.10000 0.07400 0.08000 0.06634 0.06000 0.05704 0.04000 0.04560 0.02000 0.03042 0.01000 0.02053 0.0 0.0 0.01000 -0.01280 0.02000 -0.01510 0.04000 -0.01632 0.06000 -0.01590 0.08000 -0.01564 0.10000 -0.01530 0.15000 -0.01445 0.20000 -0.01360 0.25000 -0.01275 0.30000 -0.01190 0.35000 -0.01105 0.40000 -0.01020 0.45000 -0.00935 0.50000 -0.00850 0.55000 -0.00765 0.60000 -0.00680 0.65000 -0.00595 0.70000 -0.00510 0.75000 -0.00425 0.80000 -0.00340 0.85000 -0.00255 0.90000 -0.00170 0.95000 -0.00085 1.00000 0.0 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for SPICA 11.73% smoothed (spicasm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| spicasm-il | 50,000 | 9 | 10.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| spicasm-il | 50,000 | 5 | 30.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| spicasm-il | 100,000 | 9 | 50.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| spicasm-il | 100,000 | 5 | 55.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| spicasm-il | 200,000 | 9 | 77.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| spicasm-il | 200,000 | 5 | 77.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| spicasm-il | 500,000 | 9 | 112.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| spicasm-il | 500,000 | 5 | 104.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| spicasm-il | 1,000,000 | 9 | 136.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| spicasm-il | 1,000,000 | 5 | 123.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||