REPUBLIC S-3 AIRFOIL (s3-il)
REPUBLIC S-3 AIRFOIL - Republic S-3 airfoil (P-47 wing airfoil)
| Details | Dat file | Parser | |
|
(s3-il) REPUBLIC S-3 AIRFOIL Republic S-3 airfoil (P-47 wing airfoil) Max thickness 11% at 30% chord. Max camber 1.8% at 15% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
REPUBLIC S-3 AIRFOIL
19. 19.
0.000000 0.000000
0.012500 0.019200
0.025000 0.031000
0.050000 0.044400
0.075000 0.053500
0.100000 0.060400
0.150000 0.067400
0.200000 0.070600
0.250000 0.071100
0.300000 0.070500
0.350000 0.068500
0.400000 0.065600
0.450000 0.062700
0.500000 0.058900
0.600000 0.048500
0.700000 0.035400
0.800000 0.023000
0.900000 0.010500
1.000000 0.000000
0.000000 0.000000
0.012500 -0.009300
0.025000 -0.013400
0.050000 -0.018400
0.075000 -0.022100
0.100000 -0.025300
0.150000 -0.030800
0.200000 -0.035400
0.250000 -0.038100
0.300000 -0.039500
0.350000 -0.040000
0.400000 -0.039500
0.450000 -0.037800
0.500000 -0.035600
0.600000 -0.029600
0.700000 -0.022100
0.800000 -0.013600
0.900000 -0.006000
1.000000 0.000000
|
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for REPUBLIC S-3 AIRFOIL (s3-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s3-il | 50,000 | 9 | 23.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 50,000 | 5 | 28.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3-il | 100,000 | 9 | 38.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 100,000 | 5 | 42.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3-il | 200,000 | 9 | 56.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 200,000 | 5 | 56.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3-il | 500,000 | 9 | 76.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 500,000 | 5 | 73.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s3-il | 1,000,000 | 9 | 91.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s3-il | 1,000,000 | 5 | 85.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||