CLARK YH AIRFOIL (clarkyh-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK YH AIRFOIL (clarkyh-il) Reynolds number: 200,000 Max Cl/Cd: 65.96 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkyh-il-200000.txt Download as CSV file: xf-clarkyh-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK YH AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.6964 0.05435 0.05035 -0.0468 1.0000 0.0571
-10.500 -0.7070 0.04908 0.04463 -0.0458 1.0000 0.0557
-10.250 -0.7137 0.04417 0.03933 -0.0441 1.0000 0.0557
-10.000 -0.7210 0.03978 0.03447 -0.0414 1.0000 0.0563
-9.750 -0.7212 0.03676 0.03135 -0.0384 1.0000 0.0575
-9.500 -0.7081 0.03655 0.03132 -0.0361 1.0000 0.0593
-9.250 -0.7080 0.03513 0.02974 -0.0321 1.0000 0.0604
-9.000 -0.7083 0.03316 0.02749 -0.0282 1.0000 0.0614
-8.750 -0.7001 0.03094 0.02491 -0.0256 0.9990 0.0628
-8.500 -0.6677 0.02869 0.02208 -0.0272 0.9940 0.0654
-8.250 -0.6370 0.02587 0.01892 -0.0286 0.9886 0.0676
-8.000 -0.5971 0.02468 0.01766 -0.0313 0.9839 0.0705
-7.750 -0.5595 0.02349 0.01626 -0.0332 0.9779 0.0735
-7.500 -0.5192 0.02231 0.01476 -0.0355 0.9728 0.0760
-7.250 -0.4775 0.02069 0.01302 -0.0383 0.9689 0.0789
-7.000 -0.4420 0.01981 0.01211 -0.0397 0.9611 0.0814
-6.750 -0.4026 0.01905 0.01124 -0.0418 0.9558 0.0847
-6.500 -0.3720 0.01843 0.01050 -0.0419 0.9467 0.0872
-6.250 -0.3378 0.01761 0.00958 -0.0428 0.9402 0.0894
-6.000 -0.3122 0.01684 0.00887 -0.0421 0.9296 0.0926
-5.750 -0.2856 0.01635 0.00838 -0.0414 0.9201 0.0961
-5.500 -0.2604 0.01590 0.00787 -0.0403 0.9102 0.0995
-5.250 -0.2371 0.01542 0.00736 -0.0389 0.8990 0.1029
-5.000 -0.2149 0.01483 0.00682 -0.0374 0.8888 0.1086
-4.750 -0.1920 0.01443 0.00637 -0.0359 0.8780 0.1162
-4.500 -0.1708 0.01379 0.00586 -0.0342 0.8659 0.1314
-4.250 -0.1481 0.01339 0.00578 -0.0328 0.8546 0.1896
-4.000 -0.1238 0.01328 0.00565 -0.0315 0.8440 0.2270
-3.750 -0.0992 0.01315 0.00549 -0.0305 0.8310 0.2484
-3.500 -0.0746 0.01298 0.00531 -0.0295 0.8187 0.2658
-3.250 -0.0498 0.01277 0.00512 -0.0285 0.8074 0.2806
-3.000 -0.0249 0.01256 0.00492 -0.0276 0.7960 0.2959
-2.750 0.0002 0.01236 0.00474 -0.0268 0.7825 0.3090
-2.500 0.0253 0.01215 0.00455 -0.0259 0.7690 0.3243
-2.250 0.0501 0.01190 0.00436 -0.0251 0.7552 0.3468
-2.000 0.0739 0.01156 0.00417 -0.0240 0.7417 0.3878
-1.750 0.0922 0.01082 0.00396 -0.0220 0.7284 0.5218
-1.500 0.1454 0.01003 0.00438 -0.0252 0.7136 0.9117
-1.250 0.1976 0.01036 0.00457 -0.0291 0.6976 0.9510
-1.000 0.2509 0.01065 0.00468 -0.0337 0.6816 0.9760
-0.750 0.3074 0.01080 0.00465 -0.0394 0.6657 0.9932
-0.500 0.3533 0.01083 0.00451 -0.0432 0.6508 1.0000
-0.250 0.3791 0.01089 0.00448 -0.0429 0.6374 1.0000
0.000 0.4051 0.01098 0.00448 -0.0427 0.6254 1.0000
0.250 0.4309 0.01109 0.00448 -0.0424 0.6146 1.0000
0.500 0.4568 0.01119 0.00450 -0.0421 0.6037 1.0000
0.750 0.4826 0.01128 0.00454 -0.0419 0.5925 1.0000
1.000 0.5082 0.01139 0.00457 -0.0416 0.5826 1.0000
1.250 0.5339 0.01148 0.00464 -0.0413 0.5731 1.0000
1.500 0.5594 0.01160 0.00472 -0.0410 0.5650 1.0000
1.750 0.5846 0.01169 0.00481 -0.0407 0.5560 1.0000
2.000 0.6097 0.01179 0.00489 -0.0403 0.5475 1.0000
2.250 0.6347 0.01189 0.00497 -0.0399 0.5387 1.0000
2.500 0.6595 0.01199 0.00507 -0.0394 0.5294 1.0000
2.750 0.6841 0.01209 0.00514 -0.0389 0.5204 1.0000
3.000 0.7084 0.01217 0.00525 -0.0384 0.5089 1.0000
3.250 0.7324 0.01226 0.00534 -0.0378 0.4966 1.0000
3.500 0.7562 0.01237 0.00544 -0.0372 0.4839 1.0000
3.750 0.7799 0.01252 0.00554 -0.0365 0.4713 1.0000
4.000 0.8034 0.01267 0.00570 -0.0358 0.4577 1.0000
4.250 0.8266 0.01285 0.00590 -0.0351 0.4427 1.0000
4.500 0.8493 0.01307 0.00610 -0.0344 0.4259 1.0000
4.750 0.8714 0.01332 0.00632 -0.0335 0.4066 1.0000
5.000 0.8932 0.01357 0.00658 -0.0326 0.3825 1.0000
5.250 0.9142 0.01386 0.00683 -0.0316 0.3538 1.0000
5.500 0.9344 0.01422 0.00709 -0.0305 0.3232 1.0000
5.750 0.9535 0.01469 0.00741 -0.0294 0.2987 1.0000
6.000 0.9725 0.01521 0.00783 -0.0282 0.2809 1.0000
6.250 0.9909 0.01578 0.00831 -0.0270 0.2673 1.0000
6.500 1.0090 0.01639 0.00883 -0.0257 0.2555 1.0000
6.750 1.0278 0.01692 0.00938 -0.0245 0.2438 1.0000
7.000 1.0459 0.01749 0.00994 -0.0233 0.2323 1.0000
7.250 1.0631 0.01815 0.01054 -0.0220 0.2225 1.0000
7.500 1.0815 0.01860 0.01108 -0.0208 0.2116 1.0000
7.750 1.0990 0.01908 0.01165 -0.0195 0.1999 1.0000
8.000 1.1157 0.01955 0.01218 -0.0182 0.1855 1.0000
8.250 1.1315 0.02000 0.01265 -0.0167 0.1622 1.0000
8.500 1.1391 0.02103 0.01334 -0.0143 0.1044 1.0000
8.750 1.1350 0.02287 0.01492 -0.0104 0.0813 1.0000
9.000 1.1284 0.02458 0.01659 -0.0062 0.0711 1.0000
9.250 1.1295 0.02605 0.01811 -0.0034 0.0637 1.0000
9.500 1.1310 0.02767 0.01977 -0.0012 0.0587 1.0000
9.750 1.1370 0.02911 0.02125 0.0004 0.0545 1.0000
10.000 1.1361 0.03116 0.02327 0.0022 0.0517 1.0000
10.250 1.1440 0.03265 0.02488 0.0033 0.0492 1.0000
10.500 1.1504 0.03431 0.02660 0.0043 0.0469 1.0000
10.750 1.1554 0.03614 0.02844 0.0052 0.0450 1.0000
11.000 1.1582 0.03826 0.03053 0.0064 0.0432 1.0000
11.250 1.1660 0.03998 0.03240 0.0071 0.0417 1.0000
11.500 1.1731 0.04180 0.03430 0.0078 0.0402 1.0000
11.750 1.1803 0.04364 0.03619 0.0084 0.0390 1.0000
12.000 1.1879 0.04549 0.03805 0.0091 0.0379 1.0000
12.250 1.1980 0.04729 0.03983 0.0102 0.0367 1.0000
12.500 1.2065 0.04932 0.04199 0.0110 0.0359 1.0000
12.750 1.2116 0.05154 0.04439 0.0114 0.0350 1.0000
13.000 1.2162 0.05387 0.04686 0.0117 0.0341 1.0000
13.250 1.2204 0.05625 0.04937 0.0119 0.0333 1.0000
13.500 1.2239 0.05878 0.05203 0.0121 0.0326 1.0000
13.750 1.2270 0.06142 0.05478 0.0122 0.0321 1.0000
14.000 1.2296 0.06415 0.05762 0.0123 0.0316 1.0000
14.250 1.2326 0.06699 0.06055 0.0124 0.0311 1.0000
14.500 1.2343 0.07024 0.06393 0.0126 0.0307 1.0000
14.750 1.2298 0.07441 0.06828 0.0125 0.0304 1.0000
15.000 1.2173 0.07917 0.07325 0.0115 0.0303 1.0000
15.250 1.2020 0.08423 0.07854 0.0099 0.0302 1.0000
15.500 1.1850 0.08979 0.08432 0.0078 0.0302 1.0000
15.750 1.1668 0.09589 0.09064 0.0052 0.0302 1.0000
16.000 1.1475 0.10250 0.09745 0.0022 0.0302 1.0000
16.250 1.1270 0.10966 0.10481 -0.0012 0.0302 1.0000
16.500 1.1059 0.11733 0.11266 -0.0051 0.0303 1.0000
16.750 1.0823 0.12603 0.12158 -0.0105 0.0305 1.0000
17.000 0.8681 0.20619 0.20228 -0.0463 0.0619 1.0000
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