CLARK-Y 11.7% smoothed (clarkysm-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: CLARK-Y 11.7% smoothed (clarkysm-il) Reynolds number: 100,000 Max Cl/Cd: 52.47 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkysm-il-100000.txt Download as CSV file: xf-clarkysm-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK-Y 11.7% smoothed
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 -0.3614 0.10006 0.09528 -0.0370 1.0000 0.1207
-8.500 -0.3985 0.09935 0.09475 -0.0369 1.0000 0.1218
-8.250 -0.4300 0.09837 0.09390 -0.0350 1.0000 0.1220
-8.000 -0.3946 0.09286 0.08836 -0.0318 1.0000 0.1253
-7.750 -0.3955 0.09092 0.08647 -0.0289 1.0000 0.1278
-7.500 -0.4106 0.08945 0.08509 -0.0261 1.0000 0.1299
-7.250 -0.4338 0.08819 0.08393 -0.0230 1.0000 0.1314
-7.000 -0.4579 0.08633 0.08216 -0.0219 1.0000 0.1340
-6.750 -0.5140 0.08357 0.07926 -0.0294 1.0000 0.1375
-6.500 -0.5016 0.07965 0.07552 -0.0245 1.0000 0.1391
-6.250 -0.4960 0.07766 0.07359 -0.0206 1.0000 0.1413
-6.000 -0.4964 0.07548 0.07143 -0.0187 1.0000 0.1449
-5.750 -0.5103 0.07069 0.06642 -0.0242 0.9997 0.1542
-5.500 -0.4828 0.06844 0.06428 -0.0227 0.9955 0.1600
-5.250 -0.4645 0.04640 0.04053 -0.0390 0.9879 0.0950
-5.000 -0.4330 0.04162 0.03531 -0.0415 0.9829 0.0897
-4.750 -0.4071 0.03761 0.03068 -0.0426 0.9762 0.0897
-4.500 -0.3719 0.03463 0.02687 -0.0446 0.9709 0.0925
-4.250 -0.3455 0.03205 0.02387 -0.0449 0.9637 0.0952
-4.000 -0.3083 0.03093 0.02267 -0.0472 0.9580 0.1022
-3.750 -0.2792 0.02966 0.02081 -0.0473 0.9502 0.1073
-3.500 -0.2428 0.02839 0.01957 -0.0493 0.9444 0.1163
-3.250 -0.2118 0.02737 0.01829 -0.0499 0.9369 0.1247
-3.000 -0.1754 0.02671 0.01749 -0.0515 0.9301 0.1364
-2.750 -0.1428 0.02600 0.01682 -0.0526 0.9230 0.1495
-2.500 -0.1091 0.02536 0.01621 -0.0537 0.9155 0.1651
-2.250 -0.0730 0.02479 0.01569 -0.0553 0.9089 0.1861
-2.000 -0.0431 0.02428 0.01534 -0.0557 0.9003 0.2137
-1.750 -0.0055 0.02362 0.01497 -0.0574 0.8943 0.2645
-1.500 0.0187 0.02283 0.01475 -0.0569 0.8849 0.3566
-1.250 0.1528 0.02079 0.01469 -0.0762 0.8894 1.0000
-1.000 0.1982 0.02071 0.01432 -0.0794 0.8826 1.0000
-0.750 0.2257 0.02079 0.01421 -0.0794 0.8718 1.0000
-0.500 0.2809 0.02045 0.01366 -0.0840 0.8663 1.0000
-0.250 0.3093 0.02041 0.01348 -0.0839 0.8547 1.0000
0.000 0.3703 0.01979 0.01270 -0.0894 0.8501 1.0000
0.250 0.3961 0.01974 0.01255 -0.0886 0.8382 1.0000
0.500 0.4503 0.01910 0.01179 -0.0927 0.8334 1.0000
0.750 0.4724 0.01910 0.01172 -0.0913 0.8208 1.0000
1.000 0.5011 0.01897 0.01153 -0.0909 0.8099 1.0000
1.250 0.5456 0.01844 0.01092 -0.0931 0.8029 1.0000
1.500 0.5690 0.01841 0.01084 -0.0918 0.7902 1.0000
1.750 0.5974 0.01827 0.01065 -0.0913 0.7786 1.0000
2.000 0.6393 0.01777 0.01007 -0.0929 0.7703 1.0000
2.250 0.6624 0.01774 0.01002 -0.0915 0.7565 1.0000
2.500 0.6875 0.01768 0.00992 -0.0904 0.7427 1.0000
2.750 0.7138 0.01759 0.00979 -0.0894 0.7288 1.0000
3.000 0.7406 0.01750 0.00965 -0.0886 0.7145 1.0000
3.250 0.7672 0.01744 0.00955 -0.0877 0.6996 1.0000
3.500 0.7931 0.01740 0.00946 -0.0867 0.6838 1.0000
3.750 0.8184 0.01740 0.00941 -0.0857 0.6672 1.0000
4.000 0.8434 0.01744 0.00940 -0.0846 0.6499 1.0000
4.250 0.8683 0.01752 0.00941 -0.0835 0.6324 1.0000
4.500 0.8935 0.01763 0.00944 -0.0825 0.6145 1.0000
4.750 0.9173 0.01782 0.00956 -0.0813 0.5962 1.0000
5.000 0.9378 0.01812 0.00982 -0.0796 0.5772 1.0000
5.250 0.9597 0.01845 0.01010 -0.0782 0.5595 1.0000
5.500 0.9818 0.01880 0.01040 -0.0769 0.5424 1.0000
5.750 1.0041 0.01920 0.01076 -0.0757 0.5263 1.0000
6.000 1.0263 0.01963 0.01115 -0.0745 0.5112 1.0000
6.250 1.0476 0.02003 0.01152 -0.0731 0.4956 1.0000
6.500 1.0679 0.02040 0.01185 -0.0716 0.4795 1.0000
6.750 1.0873 0.02074 0.01215 -0.0698 0.4629 1.0000
7.000 1.1060 0.02108 0.01245 -0.0680 0.4466 1.0000
7.250 1.1248 0.02148 0.01283 -0.0663 0.4317 1.0000
7.500 1.1441 0.02193 0.01330 -0.0647 0.4181 1.0000
7.750 1.1639 0.02239 0.01376 -0.0632 0.4053 1.0000
8.000 1.1840 0.02285 0.01419 -0.0618 0.3923 1.0000
8.250 1.2019 0.02331 0.01468 -0.0600 0.3790 1.0000
8.500 1.2170 0.02378 0.01524 -0.0578 0.3652 1.0000
8.750 1.2312 0.02424 0.01576 -0.0554 0.3509 1.0000
9.000 1.2439 0.02470 0.01627 -0.0528 0.3358 1.0000
9.250 1.2546 0.02517 0.01679 -0.0499 0.3197 1.0000
9.500 1.2626 0.02567 0.01728 -0.0465 0.3020 1.0000
9.750 1.2645 0.02624 0.01790 -0.0423 0.2821 1.0000
10.000 1.2605 0.02690 0.01857 -0.0371 0.2606 1.0000
10.250 1.2558 0.02780 0.01937 -0.0322 0.2376 1.0000
10.500 1.2514 0.02895 0.02045 -0.0277 0.2140 1.0000
10.750 1.2506 0.03029 0.02161 -0.0241 0.1951 1.0000
11.000 1.2528 0.03170 0.02298 -0.0212 0.1790 1.0000
11.250 1.2575 0.03316 0.02433 -0.0187 0.1666 1.0000
11.500 1.2647 0.03462 0.02577 -0.0166 0.1562 1.0000
11.750 1.2743 0.03614 0.02732 -0.0148 0.1473 1.0000
12.000 1.2886 0.03767 0.02871 -0.0136 0.1394 1.0000
12.250 1.2982 0.03922 0.03040 -0.0119 0.1326 1.0000
12.500 1.3177 0.04086 0.03196 -0.0113 0.1257 1.0000
12.750 1.3258 0.04258 0.03386 -0.0096 0.1203 1.0000
13.000 1.3556 0.04440 0.03552 -0.0100 0.1135 1.0000
13.250 1.3554 0.04638 0.03781 -0.0077 0.1098 1.0000
13.500 1.3653 0.04824 0.03975 -0.0065 0.1050 1.0000
13.750 1.3870 0.05067 0.04220 -0.0063 0.0998 1.0000
14.000 1.3803 0.05304 0.04488 -0.0040 0.0970 1.0000
14.250 1.3787 0.05545 0.04749 -0.0023 0.0938 1.0000
14.500 1.4065 0.05825 0.05016 -0.0027 0.0883 1.0000
14.750 1.3885 0.06114 0.05341 -0.0003 0.0871 1.0000
15.000 1.3705 0.06448 0.05707 0.0015 0.0857 1.0000
15.250 1.3531 0.06824 0.06112 0.0027 0.0842 1.0000
15.500 1.3373 0.07216 0.06528 0.0032 0.0826 1.0000
15.750 1.3265 0.07601 0.06931 0.0034 0.0808 1.0000
16.000 1.3462 0.07893 0.07209 0.0037 0.0764 1.0000
16.250 1.3189 0.08407 0.07750 0.0032 0.0763 1.0000
16.500 1.2893 0.09000 0.08370 0.0019 0.0762 1.0000
16.750 1.2586 0.09671 0.09066 -0.0003 0.0762 1.0000
17.000 1.2259 0.10441 0.09858 -0.0037 0.0764 1.0000
|
Polar data table (+)
Polar graphs
<< Back to CLARK-Y 11.7% smoothed (clarkysm-il)