CLARK YS AIRFOIL (clarkys-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YS AIRFOIL (clarkys-il) Reynolds number: 500,000 Max Cl/Cd: 76.53 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkys-il-500000.txt Download as CSV file: xf-clarkys-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4742 0.08575 0.08322 -0.0110 0.8136 0.0388
-10.000 -0.5120 0.07274 0.07025 -0.0181 0.8129 0.0393
-9.250 -0.7427 0.04580 0.04218 -0.0190 0.8124 0.0330
-9.000 -0.7382 0.04255 0.03874 -0.0165 0.8086 0.0315
-8.750 -0.7480 0.03797 0.03376 -0.0123 0.8049 0.0313
-8.500 -0.7508 0.03410 0.02943 -0.0083 0.8014 0.0313
-8.250 -0.7437 0.03139 0.02634 -0.0053 0.7978 0.0316
-8.000 -0.7301 0.02981 0.02444 -0.0030 0.7939 0.0320
-7.750 -0.7219 0.02658 0.02075 -0.0001 0.7903 0.0327
-7.500 -0.7041 0.02463 0.01861 0.0014 0.7871 0.0333
-7.250 -0.6828 0.02337 0.01724 0.0024 0.7834 0.0339
-7.000 -0.6604 0.02225 0.01598 0.0034 0.7795 0.0344
-6.750 -0.6371 0.02126 0.01487 0.0042 0.7760 0.0349
-6.500 -0.6134 0.02046 0.01393 0.0051 0.7727 0.0356
-6.250 -0.5886 0.01966 0.01302 0.0057 0.7689 0.0364
-6.000 -0.5632 0.01873 0.01197 0.0063 0.7648 0.0369
-5.750 -0.5374 0.01789 0.01101 0.0069 0.7611 0.0375
-5.500 -0.5114 0.01717 0.01016 0.0074 0.7578 0.0379
-5.250 -0.4848 0.01655 0.00946 0.0078 0.7539 0.0384
-5.000 -0.4583 0.01614 0.00898 0.0082 0.7492 0.0389
-4.750 -0.4320 0.01489 0.00766 0.0086 0.7448 0.0399
-4.500 -0.4065 0.01423 0.00695 0.0092 0.7407 0.0407
-4.250 -0.3805 0.01370 0.00643 0.0097 0.7349 0.0416
-4.000 -0.3547 0.01325 0.00595 0.0103 0.7300 0.0424
-3.750 -0.3290 0.01288 0.00552 0.0109 0.7259 0.0435
-3.500 -0.3028 0.01249 0.00514 0.0114 0.7199 0.0447
-3.250 -0.2766 0.01217 0.00477 0.0119 0.7143 0.0460
-3.000 -0.2509 0.01181 0.00435 0.0126 0.7092 0.0477
-2.750 -0.2248 0.01142 0.00400 0.0131 0.7024 0.0505
-2.500 -0.1984 0.01115 0.00372 0.0136 0.6970 0.0538
-2.250 -0.1720 0.01088 0.00345 0.0141 0.6920 0.0597
-2.000 -0.1461 0.01052 0.00321 0.0146 0.6856 0.0828
-1.750 -0.1211 0.01011 0.00298 0.0152 0.6800 0.1271
-1.500 -0.0966 0.00970 0.00284 0.0159 0.6732 0.1950
-1.250 -0.0725 0.00933 0.00272 0.0167 0.6665 0.2642
-1.000 -0.0490 0.00901 0.00260 0.0176 0.6601 0.3276
-0.750 -0.0298 0.00849 0.00248 0.0193 0.6529 0.4339
-0.500 -0.0314 0.00736 0.00219 0.0254 0.6472 0.6659
-0.250 -0.0116 0.00718 0.00272 0.0282 0.6396 0.8933
0.000 0.0260 0.00760 0.00308 0.0269 0.6320 0.9130
0.250 0.0618 0.00802 0.00347 0.0260 0.6228 0.9261
0.500 0.1614 0.00930 0.00463 0.0120 0.6108 0.9386
0.750 0.2530 0.01020 0.00541 -0.0004 0.5983 0.9517
1.000 0.3237 0.01044 0.00556 -0.0088 0.5852 0.9630
1.250 0.3602 0.01061 0.00569 -0.0104 0.5727 0.9708
1.500 0.4194 0.01040 0.00539 -0.0169 0.5569 0.9779
1.750 0.4462 0.01065 0.00558 -0.0166 0.5430 0.9824
2.000 0.5094 0.01009 0.00492 -0.0240 0.5233 0.9909
2.250 0.5684 0.00953 0.00428 -0.0307 0.5004 1.0000
2.500 0.5932 0.00961 0.00427 -0.0302 0.4786 1.0000
2.750 0.6179 0.00973 0.00428 -0.0296 0.4547 1.0000
3.000 0.6426 0.00987 0.00432 -0.0291 0.4304 1.0000
3.250 0.6671 0.01003 0.00438 -0.0286 0.4090 1.0000
3.500 0.6918 0.01018 0.00445 -0.0281 0.3913 1.0000
3.750 0.7165 0.01034 0.00454 -0.0276 0.3771 1.0000
4.000 0.7410 0.01052 0.00464 -0.0271 0.3636 1.0000
4.250 0.7658 0.01064 0.00475 -0.0267 0.3535 1.0000
4.500 0.7566 0.01134 0.00542 -0.0190 0.3485 0.9929
4.750 0.7780 0.01142 0.00552 -0.0178 0.3417 0.9915
5.000 0.7987 0.01160 0.00567 -0.0165 0.3345 0.9903
5.250 0.8213 0.01171 0.00581 -0.0156 0.3279 0.9898
5.500 0.8430 0.01187 0.00596 -0.0145 0.3207 0.9892
5.750 0.8635 0.01203 0.00614 -0.0131 0.3146 0.9883
6.000 0.8841 0.01216 0.00630 -0.0118 0.3079 0.9876
6.250 0.9042 0.01237 0.00648 -0.0105 0.3006 0.9870
6.500 0.9252 0.01248 0.00663 -0.0093 0.2912 0.9865
6.750 0.9458 0.01264 0.00680 -0.0080 0.2817 0.9861
7.000 0.9664 0.01283 0.00697 -0.0068 0.2709 0.9858
7.250 0.9877 0.01297 0.00713 -0.0057 0.2588 0.9856
7.500 1.0086 0.01318 0.00732 -0.0046 0.2437 0.9855
7.750 1.0292 0.01345 0.00754 -0.0036 0.2251 0.9855
8.000 1.0490 0.01385 0.00783 -0.0025 0.1983 0.9856
8.250 1.0676 0.01439 0.00824 -0.0014 0.1715 0.9858
8.500 1.0859 0.01497 0.00872 -0.0002 0.1493 0.9861
8.750 1.1042 0.01557 0.00922 0.0009 0.1295 0.9866
9.000 1.1248 0.01609 0.00969 0.0016 0.1164 0.9873
9.250 1.1447 0.01658 0.01016 0.0024 0.1066 0.9880
9.500 1.1628 0.01710 0.01067 0.0036 0.0979 0.9887
9.750 1.1807 0.01763 0.01119 0.0047 0.0896 0.9895
10.000 1.1984 0.01813 0.01170 0.0058 0.0816 0.9904
10.250 1.2144 0.01873 0.01229 0.0072 0.0732 0.9915
10.500 1.2280 0.01943 0.01294 0.0088 0.0600 0.9928
10.750 1.2364 0.02075 0.01405 0.0105 0.0338 0.9944
11.000 1.2467 0.02207 0.01531 0.0114 0.0244 0.9962
11.250 1.2531 0.02319 0.01648 0.0130 0.0220 0.9985
11.500 1.2580 0.02450 0.01788 0.0142 0.0207 1.0000
11.750 1.2476 0.02566 0.01913 0.0185 0.0201 1.0000
12.000 1.2379 0.02685 0.02039 0.0226 0.0197 1.0000
12.250 1.2280 0.02804 0.02164 0.0267 0.0193 1.0000
12.500 1.2151 0.02943 0.02309 0.0310 0.0187 1.0000
12.750 1.2026 0.03114 0.02485 0.0347 0.0181 1.0000
13.000 1.1970 0.03282 0.02661 0.0372 0.0180 1.0000
13.250 1.1853 0.03536 0.02922 0.0393 0.0174 1.0000
13.500 1.1820 0.03750 0.03144 0.0406 0.0173 1.0000
13.750 1.1803 0.03966 0.03369 0.0416 0.0169 1.0000
14.000 1.1765 0.04219 0.03631 0.0423 0.0167 1.0000
14.250 1.1722 0.04493 0.03914 0.0427 0.0164 1.0000
14.500 1.1664 0.04798 0.04228 0.0428 0.0161 1.0000
14.750 1.1616 0.05116 0.04555 0.0426 0.0158 1.0000
15.000 1.1558 0.05459 0.04907 0.0422 0.0156 1.0000
15.250 1.1494 0.05823 0.05279 0.0416 0.0154 1.0000
15.500 1.1435 0.06191 0.05655 0.0408 0.0153 1.0000
15.750 1.1368 0.06579 0.06052 0.0399 0.0151 1.0000
16.000 1.1289 0.06990 0.06470 0.0389 0.0148 1.0000
16.250 1.1224 0.07392 0.06879 0.0378 0.0147 1.0000
16.500 1.1169 0.07779 0.07273 0.0367 0.0146 1.0000
16.750 1.1100 0.08180 0.07679 0.0357 0.0144 1.0000
17.000 1.1035 0.08551 0.08054 0.0351 0.0141 1.0000
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