CLARK-Y 11.7% smoothed (clarkysm-il)
CLARK-Y 11.7% smoothed - CLARK Y airfoil (smoothed)
| Details | Dat file | Parser | |
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(clarkysm-il) CLARK-Y 11.7% smoothed CLARK Y airfoil (smoothed) Max thickness 11.7% at 30.9% chord. Max camber 3.5% at 43.5% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
CLARK-Y 11.7% smoothed 1.00000 0.0 0.99572 0.00115 0.98296 0.00448 0.96194 0.00972 0.93301 0.01656 0.89668 0.02475 0.85355 0.03400 0.80438 0.04394 0.75000 0.05412 0.69134 0.06405 0.62941 0.07319 0.56526 0.08105 0.50000 0.08719 0.43474 0.09128 0.37059 0.09312 0.33928 0.09318 0.30866 0.09266 0.27886 0.09158 0.25000 0.08996 0.22221 0.08774 0.19562 0.08483 0.17033 0.08113 0.14645 0.07660 0.12408 0.07134 0.10332 0.06552 0.08427 0.05939 0.06699 0.05313 0.05156 0.04677 0.03806 0.04027 0.02653 0.03352 0.01704 0.02652 0.00961 0.01943 0.00428 0.01254 0.00107 0.00616 0.0 0.00047 0.00107 -0.00453 0.00428 -0.00898 0.00961 -0.01296 0.01704 -0.01651 0.02653 -0.01959 0.03806 -0.02214 0.05156 -0.02414 0.06699 -0.02567 0.08427 -0.02680 0.10332 -0.02763 0.12408 -0.02816 0.14645 -0.02839 0.17033 -0.02832 0.19562 -0.02795 0.22221 -0.02734 0.25000 -0.02653 0.27886 -0.02559 0.30866 -0.02458 0.33928 -0.02351 0.37059 -0.02242 0.43474 -0.02018 0.50000 -0.01792 0.56526 -0.01566 0.62941 -0.01345 0.69134 -0.01131 0.75000 -0.00928 0.80438 -0.00741 0.85355 -0.00575 0.89668 -0.00429 0.93301 -0.00302 0.96194 -0.00190 0.98296 -0.00094 0.99572 -0.00025 1.00000 0.0 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
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Polars for CLARK-Y 11.7% smoothed (clarkysm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| clarkysm-il | 50,000 | 9 | 30 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 50,000 | 5 | 35.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkysm-il | 100,000 | 9 | 52.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 100,000 | 5 | 53.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkysm-il | 200,000 | 9 | 74.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 200,000 | 5 | 70.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkysm-il | 500,000 | 9 | 101.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 500,000 | 5 | 90.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| clarkysm-il | 1,000,000 | 9 | 119.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| clarkysm-il | 1,000,000 | 5 | 106.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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