SOMERS S102 AIRFOIL (SHARP) (s102s-il)
SOMERS S102 AIRFOIL (SHARP) - Dan Somers airfoil for the Toyota general aviation airplane
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(s102s-il) SOMERS S102 AIRFOIL (SHARP) Dan Somers airfoil for the Toyota general aviation airplane Max thickness 15% at 40% chord. Max camber 2.1% at 68.7% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
SOMERS S102 AIRFOIL (SHARP)
33. 33.
0.00001 0.00039
0.00017 0.00217
0.00357 0.01122
0.01117 0.02128
0.02281 0.03160
0.03845 0.04166
0.05803 0.05091
0.08181 0.05887
0.11019 0.06562
0.14297 0.07163
0.17954 0.07704
0.21937 0.08178
0.26191 0.08578
0.30662 0.08892
0.35296 0.09109
0.40037 0.09215
0.44828 0.09194
0.49614 0.09013
0.54379 0.08620
0.59159 0.08025
0.63946 0.07299
0.68678 0.06502
0.73290 0.05672
0.77715 0.04842
0.81885 0.04036
0.85732 0.03272
0.89191 0.02553
0.92221 0.01865
0.94818 0.01220
0.96965 0.00672
0.98603 0.00278
0.99642 0.00062
1.00000 0.00000
0.00001 0.00039
0.00009 -0.00147
0.00054 -0.00308
0.00151 -0.00454
0.00300 -0.00600
0.01018 -0.01065
0.02452 -0.01660
0.04424 -0.02243
0.06896 -0.02811
0.09830 -0.03357
0.13180 -0.03876
0.16902 -0.04357
0.20943 -0.04791
0.25250 -0.05166
0.29769 -0.05467
0.34441 -0.05678
0.39208 -0.05776
0.44011 -0.05736
0.48787 -0.05495
0.53570 -0.04955
0.58486 -0.04152
0.63544 -0.03252
0.68645 -0.02371
0.73682 -0.01572
0.78548 -0.00900
0.83135 -0.00377
0.87343 -0.00018
0.91073 0.00180
0.94228 0.00238
0.96734 0.00199
0.98544 0.00115
0.99636 0.00034
1.00000 0.00000
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Polars for SOMERS S102 AIRFOIL (SHARP) (s102s-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s102s-il | 50,000 | 9 | 30.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 50,000 | 5 | 26.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102s-il | 100,000 | 9 | 40.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 100,000 | 5 | 42.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102s-il | 200,000 | 9 | 59.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 200,000 | 5 | 57 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102s-il | 500,000 | 9 | 82.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 500,000 | 5 | 69.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s102s-il | 1,000,000 | 9 | 95.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s102s-il | 1,000,000 | 5 | 82.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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