CLARK YS AIRFOIL (clarkys-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YS AIRFOIL (clarkys-il) Reynolds number: 50,000 Max Cl/Cd: 23.2 at α=8.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkys-il-50000.txt Download as CSV file: xf-clarkys-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YS AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4384 0.11039 0.10390 0.0062 1.0000 0.2770
-9.250 -0.4378 0.10713 0.10071 0.0052 1.0000 0.2869
-9.000 -0.4584 0.10608 0.09979 0.0035 1.0000 0.2991
-8.750 -0.4269 0.10077 0.09444 0.0044 1.0000 0.3122
-8.500 -0.4170 0.09704 0.09075 0.0042 1.0000 0.3239
-8.250 -0.4153 0.09391 0.08769 0.0038 1.0000 0.3373
-8.000 -0.4124 0.09083 0.08468 0.0036 1.0000 0.3529
-7.750 -0.4018 0.08755 0.08145 0.0040 1.0000 0.3710
-7.500 -0.3935 0.08466 0.07861 0.0047 1.0000 0.3938
-7.250 -0.3936 0.08191 0.07596 0.0057 1.0000 0.4179
-7.000 -0.3731 0.07859 0.07265 0.0066 1.0000 0.4422
-5.500 -0.5915 0.06037 0.05407 0.0080 1.0000 0.2345
-5.250 -0.5813 0.06039 0.05455 0.0136 1.0000 0.2875
-5.000 -0.5835 0.06045 0.05492 0.0213 1.0000 0.3523
-4.750 -0.5889 0.04770 0.03984 0.0148 1.0000 0.1677
-4.500 -0.5800 0.04515 0.03708 0.0171 1.0000 0.1644
-4.250 -0.5710 0.04254 0.03405 0.0196 1.0000 0.1600
-4.000 -0.5599 0.04006 0.03092 0.0221 1.0000 0.1560
-3.750 -0.5457 0.03819 0.02855 0.0243 1.0000 0.1549
-3.500 -0.5294 0.03667 0.02694 0.0256 1.0000 0.1580
-3.250 -0.5125 0.03536 0.02540 0.0271 1.0000 0.1610
-3.000 -0.4941 0.03407 0.02378 0.0284 1.0000 0.1643
-2.750 -0.4731 0.03283 0.02216 0.0295 1.0000 0.1674
-2.500 -0.4304 0.03160 0.02077 0.0262 0.9931 0.1752
-2.250 -0.1002 0.02688 0.01912 -0.0234 0.9971 1.0000
-2.000 -0.0398 0.02728 0.01891 -0.0309 0.9832 1.0000
-1.750 0.0212 0.02758 0.01879 -0.0383 0.9676 1.0000
-1.500 0.0798 0.02784 0.01872 -0.0450 0.9514 1.0000
-1.250 0.1371 0.02806 0.01868 -0.0513 0.9355 1.0000
-1.000 0.1932 0.02826 0.01867 -0.0572 0.9207 1.0000
-0.750 0.2513 0.02840 0.01863 -0.0632 0.9063 1.0000
-0.500 0.3001 0.02859 0.01869 -0.0673 0.8915 1.0000
-0.250 0.3423 0.02886 0.01887 -0.0701 0.8761 1.0000
0.000 0.3766 0.02927 0.01921 -0.0712 0.8600 1.0000
0.250 0.4038 0.02983 0.01971 -0.0710 0.8429 1.0000
0.500 0.4272 0.03051 0.02035 -0.0702 0.8255 1.0000
0.750 0.4492 0.03121 0.02102 -0.0690 0.8077 1.0000
1.000 0.4707 0.03190 0.02168 -0.0675 0.7902 1.0000
1.250 0.4918 0.03257 0.02232 -0.0658 0.7732 1.0000
1.500 0.5118 0.03323 0.02296 -0.0640 0.7566 1.0000
1.750 0.5242 0.03424 0.02398 -0.0618 0.7376 1.0000
2.000 0.5405 0.03506 0.02480 -0.0599 0.7208 1.0000
2.250 0.5577 0.03582 0.02556 -0.0581 0.7050 1.0000
2.500 0.5758 0.03651 0.02626 -0.0563 0.6903 1.0000
2.750 0.5993 0.03678 0.02653 -0.0545 0.6785 1.0000
3.000 0.6136 0.03781 0.02760 -0.0529 0.6641 1.0000
3.250 0.6268 0.03896 0.02878 -0.0513 0.6502 1.0000
3.500 0.6388 0.04026 0.03011 -0.0497 0.6372 1.0000
3.750 0.6533 0.04137 0.03128 -0.0481 0.6259 1.0000
4.000 0.6784 0.04149 0.03142 -0.0464 0.6167 1.0000
4.250 0.6827 0.04348 0.03348 -0.0447 0.6038 1.0000
4.500 0.6891 0.04528 0.03533 -0.0429 0.5925 1.0000
4.750 0.7245 0.04439 0.03451 -0.0412 0.5845 1.0000
5.000 0.7201 0.04711 0.03729 -0.0392 0.5715 1.0000
5.250 0.7185 0.04945 0.03967 -0.0370 0.5598 1.0000
5.500 0.7404 0.04977 0.04006 -0.0351 0.5497 1.0000
5.750 0.7577 0.05039 0.04076 -0.0331 0.5389 1.0000
6.000 0.7397 0.05405 0.04444 -0.0305 0.5269 1.0000
6.250 0.7453 0.05566 0.04613 -0.0281 0.5160 1.0000
6.500 0.8116 0.05170 0.04234 -0.0263 0.5051 1.0000
6.750 0.7934 0.05543 0.04611 -0.0237 0.4917 1.0000
7.000 0.7367 0.06167 0.05224 -0.0196 0.4816 1.0000
7.250 0.7486 0.06254 0.05319 -0.0170 0.4686 1.0000
7.500 0.7708 0.06253 0.05330 -0.0147 0.4540 1.0000
7.750 0.7970 0.06194 0.05284 -0.0121 0.4385 1.0000
8.000 0.8306 0.06039 0.05144 -0.0093 0.4223 1.0000
8.250 0.9160 0.05343 0.04477 -0.0065 0.4032 1.0000
8.500 1.0305 0.04442 0.03573 -0.0057 0.3802 1.0000
8.750 1.0386 0.04566 0.03706 -0.0030 0.3632 1.0000
9.000 1.0500 0.04676 0.03824 -0.0004 0.3471 1.0000
9.250 1.0642 0.04776 0.03928 0.0020 0.3317 1.0000
9.500 1.0069 0.05425 0.04601 0.0070 0.3258 1.0000
9.750 0.9481 0.06080 0.05253 0.0114 0.3215 1.0000
10.000 0.8754 0.06973 0.06129 0.0135 0.3185 1.0000
10.250 0.7666 0.08686 0.07804 0.0090 0.3160 1.0000
10.500 0.7178 0.09626 0.08730 0.0065 0.3135 1.0000
10.750 0.6946 0.10252 0.09351 0.0052 0.3103 1.0000
11.000 0.7149 0.10360 0.09468 0.0071 0.2998 1.0000
11.250 0.6950 0.10987 0.10092 0.0055 0.2990 1.0000
11.500 0.6903 0.11506 0.10613 0.0046 0.3003 1.0000
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Polar data table (+)
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