CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK K AIRFOIL (clarkk-il) Reynolds number: 100,000 Max Cl/Cd: 54.06 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkk-il-100000.txt Download as CSV file: xf-clarkk-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK K 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4074 0.10020 0.09515 -0.0382 1.0000 0.1537
-8.500 -0.3634 0.09529 0.09014 -0.0345 1.0000 0.1593
-8.250 -0.3700 0.09354 0.08847 -0.0335 1.0000 0.1655
-8.000 -0.4176 0.09354 0.08870 -0.0317 1.0000 0.1682
-7.750 -0.4720 0.09286 0.08817 -0.0324 1.0000 0.1691
-7.500 -0.4020 0.08791 0.08312 -0.0263 1.0000 0.1762
-7.250 -0.4248 0.08697 0.08228 -0.0227 1.0000 0.1798
-7.000 -0.4907 0.08618 0.08161 -0.0270 1.0000 0.1847
-6.750 -0.4786 0.08262 0.07813 -0.0219 1.0000 0.1872
-6.500 -0.4683 0.08091 0.07646 -0.0173 1.0000 0.1913
-6.250 -0.5042 0.07811 0.07358 -0.0240 1.0000 0.2021
-6.000 -0.4914 0.07562 0.07120 -0.0181 1.0000 0.2045
-5.750 -0.4856 0.07404 0.06967 -0.0145 1.0000 0.2103
-5.500 -0.4929 0.07060 0.06617 -0.0175 1.0000 0.2210
-5.250 -0.4804 0.06867 0.06428 -0.0152 0.9989 0.2272
-5.000 -0.4498 0.06441 0.05990 -0.0217 0.9926 0.2411
-4.750 -0.4125 0.06143 0.05651 -0.0331 0.9840 0.2693
-4.500 -0.3888 0.05723 0.05247 -0.0324 0.9789 0.2726
-4.250 -0.3229 0.03686 0.02960 -0.0540 0.9746 0.1370
-4.000 -0.2785 0.03291 0.02465 -0.0577 0.9707 0.1249
-3.750 -0.2443 0.03110 0.02255 -0.0596 0.9640 0.1241
-3.500 -0.2037 0.02944 0.02062 -0.0623 0.9584 0.1227
-3.250 -0.1650 0.02812 0.01904 -0.0646 0.9526 0.1210
-3.000 -0.1283 0.02708 0.01776 -0.0664 0.9454 0.1200
-2.750 -0.0830 0.02619 0.01669 -0.0696 0.9407 0.1199
-2.500 -0.0537 0.02565 0.01607 -0.0701 0.9315 0.1216
-2.250 -0.0101 0.02502 0.01537 -0.0730 0.9260 0.1233
-2.000 0.0201 0.02460 0.01494 -0.0735 0.9171 0.1240
-1.750 0.0614 0.02408 0.01442 -0.0759 0.9108 0.1253
-1.500 0.0925 0.02368 0.01413 -0.0766 0.9023 0.1274
-1.250 0.1317 0.02327 0.01378 -0.0786 0.8953 0.1312
-1.000 0.1648 0.02309 0.01361 -0.0796 0.8869 0.1377
-0.750 0.2032 0.02272 0.01338 -0.0814 0.8795 0.1500
-0.250 0.2751 0.02162 0.01316 -0.0844 0.8640 0.3377
0.000 0.3093 0.01993 0.01310 -0.0841 0.8602 0.7636
0.250 0.3641 0.01973 0.01309 -0.0885 0.8509 1.0000
0.500 0.4072 0.01944 0.01265 -0.0905 0.8449 1.0000
0.750 0.4318 0.01956 0.01266 -0.0897 0.8331 1.0000
1.000 0.4747 0.01915 0.01212 -0.0915 0.8274 1.0000
1.250 0.4977 0.01925 0.01214 -0.0902 0.8147 1.0000
1.500 0.5267 0.01916 0.01197 -0.0898 0.8042 1.0000
1.750 0.5635 0.01872 0.01144 -0.0903 0.7957 1.0000
2.000 0.5886 0.01866 0.01132 -0.0892 0.7826 1.0000
2.250 0.6168 0.01850 0.01109 -0.0885 0.7707 1.0000
2.500 0.6526 0.01804 0.01054 -0.0887 0.7618 1.0000
2.750 0.6764 0.01806 0.01054 -0.0875 0.7480 1.0000
3.000 0.7017 0.01807 0.01052 -0.0864 0.7348 1.0000
3.250 0.7290 0.01801 0.01041 -0.0857 0.7222 1.0000
3.500 0.7587 0.01785 0.01020 -0.0852 0.7102 1.0000
3.750 0.7865 0.01778 0.01008 -0.0845 0.6969 1.0000
4.000 0.8115 0.01782 0.01010 -0.0834 0.6818 1.0000
4.250 0.8369 0.01785 0.01012 -0.0824 0.6664 1.0000
4.500 0.8624 0.01788 0.01013 -0.0814 0.6503 1.0000
4.750 0.8881 0.01792 0.01013 -0.0805 0.6337 1.0000
5.000 0.9138 0.01798 0.01015 -0.0795 0.6164 1.0000
5.250 0.9394 0.01806 0.01017 -0.0785 0.5981 1.0000
5.500 0.9615 0.01827 0.01039 -0.0771 0.5772 1.0000
5.750 0.9850 0.01848 0.01057 -0.0759 0.5562 1.0000
6.000 1.0096 0.01872 0.01070 -0.0748 0.5353 1.0000
6.250 1.0315 0.01908 0.01103 -0.0735 0.5128 1.0000
6.500 1.0537 0.01949 0.01139 -0.0722 0.4905 1.0000
6.750 1.0770 0.01995 0.01173 -0.0711 0.4698 1.0000
7.000 1.0983 0.02050 0.01225 -0.0698 0.4491 1.0000
7.250 1.1195 0.02107 0.01281 -0.0686 0.4296 1.0000
7.500 1.1403 0.02161 0.01332 -0.0672 0.4105 1.0000
7.750 1.1602 0.02210 0.01373 -0.0658 0.3911 1.0000
8.000 1.1782 0.02257 0.01411 -0.0640 0.3710 1.0000
8.250 1.1930 0.02303 0.01462 -0.0619 0.3500 1.0000
8.500 1.2081 0.02352 0.01509 -0.0598 0.3302 1.0000
8.750 1.2237 0.02409 0.01565 -0.0579 0.3127 1.0000
9.000 1.2390 0.02470 0.01629 -0.0559 0.2965 1.0000
9.250 1.2525 0.02533 0.01695 -0.0538 0.2798 1.0000
9.500 1.2635 0.02598 0.01765 -0.0513 0.2624 1.0000
9.750 1.2703 0.02668 0.01845 -0.0482 0.2420 1.0000
10.000 1.2703 0.02751 0.01931 -0.0443 0.2177 1.0000
10.250 1.2643 0.02885 0.02060 -0.0400 0.1801 1.0000
10.500 1.2523 0.03116 0.02257 -0.0357 0.1329 1.0000
10.750 1.2449 0.03366 0.02480 -0.0324 0.1091 1.0000
11.000 1.2421 0.03599 0.02702 -0.0298 0.0969 1.0000
11.250 1.2402 0.03834 0.02928 -0.0275 0.0896 1.0000
11.500 1.2441 0.04038 0.03138 -0.0255 0.0836 1.0000
11.750 1.2471 0.04263 0.03347 -0.0236 0.0792 1.0000
12.000 1.2561 0.04446 0.03547 -0.0221 0.0751 1.0000
12.250 1.2650 0.04634 0.03734 -0.0207 0.0713 1.0000
12.500 1.2828 0.04814 0.03901 -0.0193 0.0678 1.0000
12.750 1.2975 0.05001 0.04109 -0.0180 0.0656 1.0000
13.000 1.3117 0.05201 0.04324 -0.0169 0.0634 1.0000
13.250 1.3268 0.05402 0.04529 -0.0159 0.0611 1.0000
13.500 1.3566 0.05653 0.04771 -0.0156 0.0584 1.0000
13.750 1.3564 0.05924 0.05075 -0.0141 0.0575 1.0000
14.000 1.3566 0.06229 0.05410 -0.0127 0.0569 1.0000
14.250 1.3530 0.06566 0.05777 -0.0115 0.0565 1.0000
14.500 1.3452 0.06938 0.06179 -0.0105 0.0561 1.0000
14.750 1.3334 0.07349 0.06619 -0.0099 0.0560 1.0000
15.000 1.3179 0.07802 0.07101 -0.0097 0.0559 1.0000
15.250 1.2990 0.08307 0.07633 -0.0102 0.0559 1.0000
15.500 1.2769 0.08872 0.08225 -0.0113 0.0560 1.0000
15.750 1.2522 0.09505 0.08885 -0.0134 0.0562 1.0000
16.000 1.2253 0.10220 0.09624 -0.0164 0.0566 1.0000
16.250 1.1967 0.11027 0.10454 -0.0205 0.0571 1.0000
16.500 1.1673 0.11933 0.11379 -0.0256 0.0577 1.0000
16.750 1.1393 0.12901 0.12361 -0.0313 0.0583 1.0000
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