CLARK YM-18 AIRFOIL (clarym18-il)
CLARK YM-18 AIRFOIL - CLARK YM18 airfoil
| Details | Dat file | Parser | |
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(clarym18-il) CLARK YM-18 AIRFOIL CLARK YM18 airfoil Max thickness 18% at 29.6% chord. Max camber 3.6% at 39.6% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Lednicer format |
CLARK YM-18 AIRFOIL
17. 17.
0.0000000 0.0000000
0.0114900 0.0294000
0.0234700 0.0444100
0.0477800 0.0644400
0.0723100 0.0780900
0.0969400 0.0890300
0.1463800 0.1052400
0.1960200 0.1158400
0.2957500 0.1236700
0.3957600 0.1233100
0.4960200 0.1155600
0.5965000 0.1016200
0.6971700 0.0822800
0.7979800 0.0586500
0.8989200 0.0315200
0.9494300 0.0166600
1.0000000 0.0009000
0.0000000 0.0000000
0.0133500 -.0247400
0.0261400 -.0330000
0.0514700 -.0426300
0.0766600 -.0481600
0.1017900 -.0520000
0.1519500 -.0566700
0.2020000 -.0582500
0.3019300 -.0561100
0.4017800 -.0518800
0.5015800 -.0460500
0.6013400 -.0389100
0.7010601 -.0306800
0.8007400 -.0214500
0.9004000 -.0115300
0.9502200 -.0063100
1.0000000 -.0009000
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Polars for CLARK YM-18 AIRFOIL (clarym18-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| clarym18-il | 50,000 | 9 | 7.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 50,000 | 5 | 25.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 100,000 | 9 | 43.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 100,000 | 5 | 43.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 200,000 | 9 | 60.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 200,000 | 5 | 56 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 500,000 | 9 | 77.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 500,000 | 5 | 73.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarym18-il | 1,000,000 | 9 | 96.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarym18-il | 1,000,000 | 5 | 93.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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