CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK Z AIRFOIL (clarkz-il) Reynolds number: 100,000 Max Cl/Cd: 54.02 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkz-il-100000.txt Download as CSV file: xf-clarkz-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK Z AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3364 0.09620 0.09138 -0.0319 1.0000 0.1146
-7.750 -0.3480 0.09481 0.09008 -0.0293 1.0000 0.1164
-7.500 -0.3662 0.09376 0.08914 -0.0262 1.0000 0.1180
-7.250 -0.3902 0.09299 0.08848 -0.0227 1.0000 0.1193
-7.000 -0.4139 0.09179 0.08738 -0.0214 1.0000 0.1211
-6.750 -0.4556 0.09063 0.08620 -0.0285 1.0000 0.1237
-6.500 -0.4606 0.08666 0.08227 -0.0279 1.0000 0.1248
-6.250 -0.4548 0.08388 0.07959 -0.0233 1.0000 0.1260
-6.000 -0.4457 0.08148 0.07722 -0.0211 0.9988 0.1281
-5.750 -0.4119 0.07584 0.07118 -0.0390 0.9882 0.1407
-5.500 -0.3880 0.07195 0.06748 -0.0369 0.9845 0.1432
-5.250 -0.3618 0.06914 0.06466 -0.0387 0.9781 0.1494
-5.000 -0.3288 0.06417 0.05948 -0.0476 0.9707 0.1602
-4.750 -0.3044 0.06154 0.05684 -0.0491 0.9628 0.1668
-4.500 -0.2691 0.05754 0.05267 -0.0553 0.9566 0.1791
-4.250 -0.2435 0.05462 0.04954 -0.0590 0.9470 0.1939
-4.000 -0.2061 0.05167 0.04647 -0.0634 0.9416 0.2110
-3.750 -0.1834 0.04954 0.04427 -0.0643 0.9320 0.2284
-3.500 -0.1483 0.04701 0.04177 -0.0666 0.9266 0.2488
-3.250 -0.0779 0.03513 0.02747 -0.0766 0.9216 0.1064
-3.000 -0.0430 0.03274 0.02476 -0.0782 0.9140 0.1028
-2.750 0.0042 0.03055 0.02212 -0.0816 0.9097 0.1015
-2.500 0.0325 0.02949 0.02081 -0.0817 0.8998 0.1036
-2.250 0.0784 0.02801 0.01901 -0.0845 0.8947 0.1053
-2.000 0.1105 0.02708 0.01786 -0.0850 0.8857 0.1072
-1.750 0.1538 0.02575 0.01646 -0.0874 0.8797 0.1113
-1.500 0.2049 0.02469 0.01538 -0.0911 0.8763 0.1223
-1.250 0.2289 0.02402 0.01484 -0.0902 0.8646 0.1310
-1.000 0.2741 0.02282 0.01373 -0.0925 0.8604 0.1567
-0.750 0.2973 0.02189 0.01323 -0.0915 0.8490 0.2154
-0.500 0.3645 0.01879 0.01247 -0.0969 0.8469 1.0000
-0.250 0.3934 0.01876 0.01221 -0.0966 0.8366 1.0000
0.000 0.4306 0.01846 0.01170 -0.0975 0.8289 1.0000
0.250 0.4551 0.01852 0.01161 -0.0965 0.8171 1.0000
0.500 0.4942 0.01811 0.01103 -0.0976 0.8107 1.0000
0.750 0.5166 0.01820 0.01101 -0.0962 0.7977 1.0000
1.000 0.5429 0.01820 0.01090 -0.0954 0.7863 1.0000
1.250 0.5778 0.01786 0.01043 -0.0957 0.7782 1.0000
1.500 0.6010 0.01795 0.01045 -0.0945 0.7649 1.0000
1.750 0.6271 0.01797 0.01038 -0.0936 0.7528 1.0000
2.000 0.6589 0.01776 0.01006 -0.0935 0.7430 1.0000
2.250 0.6849 0.01777 0.01000 -0.0926 0.7301 1.0000
2.500 0.7096 0.01787 0.01003 -0.0916 0.7165 1.0000
2.750 0.7356 0.01793 0.01003 -0.0907 0.7034 1.0000
3.000 0.7634 0.01794 0.00995 -0.0901 0.6910 1.0000
3.250 0.7925 0.01790 0.00981 -0.0897 0.6789 1.0000
3.500 0.8167 0.01808 0.00995 -0.0887 0.6643 1.0000
3.750 0.8413 0.01827 0.01010 -0.0878 0.6499 1.0000
4.000 0.8664 0.01846 0.01024 -0.0869 0.6358 1.0000
4.250 0.8919 0.01865 0.01039 -0.0861 0.6220 1.0000
4.500 0.9181 0.01883 0.01050 -0.0854 0.6086 1.0000
4.750 0.9455 0.01899 0.01057 -0.0849 0.5958 1.0000
5.000 0.9696 0.01927 0.01083 -0.0840 0.5815 1.0000
5.250 0.9931 0.01958 0.01114 -0.0831 0.5671 1.0000
5.500 1.0168 0.01988 0.01141 -0.0821 0.5527 1.0000
5.750 1.0407 0.02011 0.01162 -0.0811 0.5376 1.0000
6.000 1.0640 0.02029 0.01174 -0.0799 0.5212 1.0000
6.250 1.0868 0.02046 0.01185 -0.0787 0.5043 1.0000
6.500 1.1093 0.02071 0.01206 -0.0775 0.4883 1.0000
6.750 1.1318 0.02106 0.01240 -0.0765 0.4738 1.0000
7.000 1.1543 0.02143 0.01275 -0.0754 0.4597 1.0000
7.250 1.1768 0.02180 0.01311 -0.0744 0.4456 1.0000
7.500 1.1988 0.02219 0.01348 -0.0733 0.4311 1.0000
7.750 1.2201 0.02259 0.01385 -0.0721 0.4163 1.0000
8.000 1.2405 0.02302 0.01426 -0.0707 0.4011 1.0000
8.250 1.2592 0.02346 0.01473 -0.0692 0.3849 1.0000
8.500 1.2757 0.02394 0.01525 -0.0673 0.3676 1.0000
8.750 1.2903 0.02445 0.01581 -0.0651 0.3489 1.0000
9.000 1.3033 0.02501 0.01640 -0.0627 0.3288 1.0000
9.250 1.3149 0.02565 0.01698 -0.0602 0.3076 1.0000
9.500 1.3232 0.02647 0.01777 -0.0572 0.2844 1.0000
9.750 1.3297 0.02741 0.01862 -0.0541 0.2616 1.0000
10.000 1.3359 0.02850 0.01954 -0.0510 0.2418 1.0000
10.250 1.3428 0.02969 0.02066 -0.0482 0.2248 1.0000
10.500 1.3537 0.03094 0.02179 -0.0460 0.2114 1.0000
10.750 1.3663 0.03217 0.02301 -0.0442 0.2003 1.0000
11.000 1.3802 0.03349 0.02437 -0.0426 0.1911 1.0000
11.250 1.4011 0.03479 0.02551 -0.0419 0.1832 1.0000
11.500 1.4130 0.03613 0.02705 -0.0401 0.1766 1.0000
11.750 1.4394 0.03746 0.02826 -0.0403 0.1704 1.0000
12.000 1.4540 0.03903 0.03004 -0.0389 0.1657 1.0000
12.250 1.4674 0.04044 0.03158 -0.0374 0.1606 1.0000
12.500 1.4941 0.04192 0.03293 -0.0378 0.1545 1.0000
12.750 1.4923 0.04349 0.03482 -0.0347 0.1506 1.0000
13.000 1.4990 0.04485 0.03627 -0.0327 0.1455 1.0000
13.250 1.5129 0.04634 0.03771 -0.0317 0.1397 1.0000
13.500 1.5051 0.04817 0.03983 -0.0287 0.1359 1.0000
13.750 1.5110 0.04953 0.04121 -0.0271 0.1307 1.0000
14.000 1.5192 0.05137 0.04310 -0.0258 0.1260 1.0000
14.250 1.5100 0.05374 0.04578 -0.0234 0.1230 1.0000
14.500 1.5086 0.05581 0.04799 -0.0219 0.1191 1.0000
14.750 1.5245 0.05739 0.04946 -0.0213 0.1137 1.0000
15.000 1.5072 0.06055 0.05298 -0.0193 0.1113 1.0000
15.250 1.4940 0.06371 0.05639 -0.0180 0.1081 1.0000
15.500 1.0945 0.13557 0.13005 -0.0482 0.1433 1.0000
15.750 1.0739 0.14587 0.14035 -0.0528 0.1422 1.0000
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Polar data table (+)
Polar graphs
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