CLARK YS AIRFOIL (clarkys-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK YS AIRFOIL (clarkys-il) Reynolds number: 100,000 Max Cl/Cd: 46.98 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkys-il-100000-n5.txt Download as CSV file: xf-clarkys-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5168 0.09642 0.09174 -0.0101 1.0000 0.0479
-10.000 -0.5222 0.09095 0.08632 -0.0134 1.0000 0.0475
-9.750 -0.5319 0.08474 0.08016 -0.0179 1.0000 0.0470
-9.500 -0.5486 0.07745 0.07291 -0.0238 1.0000 0.0463
-9.250 -0.5735 0.06994 0.06536 -0.0277 1.0000 0.0457
-9.000 -0.6010 0.06329 0.05859 -0.0281 1.0000 0.0452
-8.750 -0.6139 0.05701 0.05199 -0.0289 0.9335 0.0451
-8.500 -0.6154 0.05268 0.04732 -0.0284 0.9096 0.0458
-8.250 -0.6156 0.04909 0.04336 -0.0267 0.8949 0.0468
-7.750 -0.6123 0.04219 0.03557 -0.0217 0.8749 0.0480
-7.500 -0.6055 0.03923 0.03213 -0.0191 0.8674 0.0483
-7.250 -0.5947 0.03659 0.02902 -0.0168 0.8600 0.0488
-7.000 -0.5810 0.03436 0.02632 -0.0147 0.8537 0.0495
-6.750 -0.5642 0.03248 0.02393 -0.0129 0.8470 0.0508
-6.500 -0.5450 0.03082 0.02191 -0.0114 0.8411 0.0519
-6.250 -0.5229 0.02937 0.02029 -0.0106 0.8354 0.0527
-6.000 -0.4996 0.02810 0.01884 -0.0099 0.8294 0.0535
-5.750 -0.4758 0.02700 0.01754 -0.0091 0.8243 0.0544
-5.500 -0.4504 0.02595 0.01632 -0.0087 0.8182 0.0555
-5.250 -0.4248 0.02499 0.01521 -0.0081 0.8127 0.0567
-5.000 -0.3989 0.02418 0.01424 -0.0077 0.8075 0.0585
-4.750 -0.3720 0.02347 0.01338 -0.0074 0.8014 0.0611
-4.500 -0.3459 0.02270 0.01252 -0.0070 0.7964 0.0631
-4.250 -0.3200 0.02202 0.01185 -0.0066 0.7906 0.0652
-4.000 -0.2947 0.02144 0.01125 -0.0061 0.7848 0.0677
-3.750 -0.2700 0.02093 0.01065 -0.0053 0.7799 0.0710
-3.500 -0.2446 0.02042 0.01010 -0.0048 0.7733 0.0752
-3.250 -0.2205 0.01993 0.00962 -0.0040 0.7680 0.0816
-3.000 -0.1948 0.01947 0.00920 -0.0036 0.7620 0.0933
-2.750 -0.1690 0.01899 0.00882 -0.0031 0.7557 0.1135
-2.500 -0.1432 0.01851 0.00848 -0.0027 0.7496 0.1474
-2.250 -0.1136 0.01801 0.00825 -0.0030 0.7410 0.2044
-2.000 -0.0817 0.01737 0.00804 -0.0038 0.7320 0.3085
-1.750 -0.0556 0.01620 0.00778 -0.0034 0.7234 0.4984
-1.500 0.0421 0.01710 0.00964 -0.0134 0.7143 0.9141
-1.250 0.1180 0.01767 0.00995 -0.0216 0.7075 0.9554
-1.000 0.2095 0.01723 0.00931 -0.0341 0.6981 0.9900
-0.750 0.2565 0.01676 0.00867 -0.0380 0.6910 1.0000
-0.500 0.2813 0.01671 0.00856 -0.0375 0.6813 1.0000
-0.250 0.3052 0.01662 0.00836 -0.0366 0.6737 1.0000
0.000 0.3297 0.01657 0.00824 -0.0359 0.6637 1.0000
0.250 0.3540 0.01651 0.00811 -0.0352 0.6547 1.0000
0.500 0.3781 0.01645 0.00796 -0.0343 0.6456 1.0000
0.750 0.4026 0.01642 0.00789 -0.0336 0.6347 1.0000
1.000 0.4267 0.01637 0.00777 -0.0328 0.6246 1.0000
1.250 0.4509 0.01633 0.00765 -0.0319 0.6136 1.0000
1.500 0.4753 0.01633 0.00763 -0.0312 0.6013 1.0000
1.750 0.4997 0.01634 0.00759 -0.0305 0.5894 1.0000
2.000 0.5238 0.01634 0.00754 -0.0296 0.5768 1.0000
2.250 0.5478 0.01637 0.00750 -0.0288 0.5637 1.0000
2.500 0.5719 0.01641 0.00749 -0.0280 0.5497 1.0000
2.750 0.5961 0.01649 0.00754 -0.0273 0.5352 1.0000
3.000 0.6202 0.01659 0.00762 -0.0265 0.5206 1.0000
3.250 0.6442 0.01672 0.00770 -0.0258 0.5058 1.0000
3.500 0.6680 0.01686 0.00781 -0.0250 0.4910 1.0000
3.750 0.6919 0.01703 0.00796 -0.0243 0.4770 1.0000
4.000 0.7156 0.01722 0.00812 -0.0236 0.4639 1.0000
4.250 0.7392 0.01743 0.00830 -0.0228 0.4511 1.0000
4.500 0.7625 0.01766 0.00849 -0.0220 0.4381 1.0000
4.750 0.7857 0.01791 0.00871 -0.0213 0.4250 1.0000
5.000 0.8088 0.01817 0.00898 -0.0205 0.4123 1.0000
5.250 0.8318 0.01846 0.00929 -0.0198 0.4009 1.0000
5.500 0.8543 0.01876 0.00957 -0.0189 0.3897 1.0000
5.750 0.8763 0.01908 0.00985 -0.0180 0.3771 1.0000
6.000 0.8981 0.01942 0.01021 -0.0172 0.3636 1.0000
6.250 0.9197 0.01978 0.01061 -0.0163 0.3507 1.0000
6.500 0.9411 0.02015 0.01102 -0.0153 0.3399 1.0000
7.000 0.9828 0.02093 0.01193 -0.0134 0.3194 1.0000
7.250 1.0030 0.02135 0.01243 -0.0123 0.3090 1.0000
7.500 1.0223 0.02180 0.01290 -0.0111 0.2979 1.0000
7.750 1.0412 0.02224 0.01348 -0.0099 0.2853 1.0000
8.000 1.0595 0.02270 0.01406 -0.0086 0.2727 1.0000
8.250 1.0767 0.02320 0.01468 -0.0072 0.2597 1.0000
8.500 1.0927 0.02373 0.01531 -0.0056 0.2454 1.0000
8.750 1.1071 0.02433 0.01598 -0.0038 0.2298 1.0000
9.000 1.1191 0.02501 0.01668 -0.0018 0.2125 1.0000
9.250 1.1281 0.02582 0.01746 0.0006 0.1954 1.0000
9.500 1.1342 0.02675 0.01834 0.0033 0.1802 1.0000
9.750 1.1381 0.02773 0.01932 0.0062 0.1673 1.0000
10.000 1.1397 0.02873 0.02033 0.0095 0.1564 1.0000
10.250 1.1373 0.02979 0.02138 0.0132 0.1488 1.0000
10.500 1.1304 0.03072 0.02237 0.0177 0.1421 1.0000
10.750 1.1201 0.03186 0.02352 0.0221 0.1374 1.0000
11.000 1.1145 0.03306 0.02479 0.0256 0.1314 1.0000
11.250 1.1090 0.03442 0.02618 0.0287 0.1256 1.0000
11.500 1.1037 0.03592 0.02771 0.0315 0.1201 1.0000
11.750 1.1019 0.03738 0.02927 0.0337 0.1149 1.0000
12.000 1.0972 0.03917 0.03108 0.0358 0.1100 1.0000
12.250 1.0952 0.04093 0.03295 0.0375 0.1049 1.0000
12.500 1.0908 0.04305 0.03513 0.0389 0.0986 1.0000
12.750 1.0856 0.04539 0.03751 0.0399 0.0932 1.0000
13.000 1.0817 0.04781 0.04004 0.0407 0.0871 1.0000
13.250 1.0731 0.05083 0.04306 0.0411 0.0824 1.0000
13.500 1.0700 0.05351 0.04593 0.0414 0.0762 1.0000
13.750 1.0615 0.05692 0.04939 0.0412 0.0716 1.0000
14.000 1.0552 0.06025 0.05285 0.0409 0.0661 1.0000
14.250 1.0443 0.06444 0.05711 0.0400 0.0601 1.0000
14.500 1.0348 0.06866 0.06143 0.0390 0.0534 1.0000
14.750 1.0229 0.07336 0.06617 0.0376 0.0493 1.0000
15.000 1.0121 0.07809 0.07098 0.0362 0.0442 1.0000
15.250 1.0008 0.08300 0.07593 0.0346 0.0414 1.0000
15.500 0.9898 0.08801 0.08102 0.0329 0.0386 1.0000
15.750 0.9788 0.09312 0.08619 0.0312 0.0361 1.0000
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