CLARK W AIRFOIL (clarkw-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK W AIRFOIL (clarkw-il) Reynolds number: 500,000 Max Cl/Cd: 98.74 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkw-il-500000.txt Download as CSV file: xf-clarkw-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK W 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.3212 0.08831 0.08613 -0.0401 0.9986 0.0419
-9.500 -0.3111 0.08456 0.08238 -0.0425 0.9971 0.0429
-9.250 -0.5941 0.03731 0.03372 -0.0824 0.9844 0.0341
-9.000 -0.5712 0.03458 0.03067 -0.0842 0.9811 0.0339
-8.750 -0.5516 0.03154 0.02733 -0.0851 0.9762 0.0338
-8.500 -0.5284 0.02822 0.02360 -0.0867 0.9732 0.0339
-8.250 -0.5040 0.02431 0.01928 -0.0884 0.9713 0.0343
-8.000 -0.4727 0.02214 0.01688 -0.0902 0.9702 0.0346
-7.750 -0.4510 0.02074 0.01532 -0.0895 0.9639 0.0349
-7.500 -0.4201 0.01943 0.01388 -0.0906 0.9613 0.0353
-7.250 -0.3881 0.01831 0.01264 -0.0918 0.9592 0.0357
-7.000 -0.3556 0.01734 0.01156 -0.0930 0.9572 0.0363
-6.750 -0.3288 0.01663 0.01077 -0.0929 0.9525 0.0369
-6.500 -0.3015 0.01591 0.00997 -0.0929 0.9476 0.0376
-6.250 -0.2714 0.01513 0.00910 -0.0933 0.9442 0.0380
-6.000 -0.2409 0.01443 0.00831 -0.0938 0.9413 0.0385
-5.750 -0.2177 0.01390 0.00772 -0.0928 0.9342 0.0389
-5.500 -0.1896 0.01335 0.00710 -0.0927 0.9294 0.0394
-5.000 -0.1375 0.01227 0.00591 -0.0917 0.9181 0.0405
-4.750 -0.1110 0.01167 0.00529 -0.0913 0.9127 0.0418
-4.500 -0.0847 0.01129 0.00489 -0.0909 0.9064 0.0430
-4.250 -0.0586 0.01094 0.00450 -0.0903 0.8984 0.0441
-4.000 -0.0319 0.01062 0.00412 -0.0898 0.8904 0.0454
-3.750 -0.0055 0.01035 0.00380 -0.0892 0.8819 0.0467
-3.500 0.0215 0.01003 0.00345 -0.0888 0.8749 0.0494
-3.250 0.0480 0.00978 0.00320 -0.0884 0.8669 0.0534
-3.000 0.0752 0.00949 0.00295 -0.0880 0.8598 0.0660
-2.750 0.1010 0.00915 0.00279 -0.0875 0.8514 0.1050
-2.500 0.1283 0.00897 0.00264 -0.0873 0.8441 0.1301
-2.250 0.1546 0.00878 0.00253 -0.0869 0.8354 0.1525
-2.000 0.1817 0.00861 0.00243 -0.0866 0.8279 0.1815
-1.750 0.2081 0.00845 0.00236 -0.0862 0.8191 0.2136
-1.500 0.2351 0.00833 0.00231 -0.0859 0.8110 0.2476
-1.250 0.2619 0.00824 0.00228 -0.0855 0.8019 0.2761
-1.000 0.2889 0.00818 0.00225 -0.0852 0.7931 0.3011
-0.500 0.3427 0.00808 0.00221 -0.0845 0.7740 0.3442
-0.250 0.3697 0.00805 0.00217 -0.0842 0.7646 0.3649
0.000 0.3962 0.00799 0.00216 -0.0838 0.7535 0.3864
0.500 0.4489 0.00787 0.00210 -0.0829 0.7316 0.4307
0.750 0.4741 0.00771 0.00207 -0.0823 0.7191 0.4760
1.000 0.4874 0.00660 0.00224 -0.0787 0.7072 0.8988
1.250 0.5313 0.00673 0.00237 -0.0816 0.6931 0.9681
1.500 0.5874 0.00688 0.00243 -0.0875 0.6767 0.9879
1.750 0.6365 0.00700 0.00245 -0.0921 0.6589 0.9969
2.000 0.6715 0.00711 0.00246 -0.0936 0.6398 1.0000
2.250 0.6948 0.00725 0.00250 -0.0926 0.6209 1.0000
2.500 0.7180 0.00739 0.00255 -0.0916 0.6014 1.0000
2.750 0.7406 0.00754 0.00262 -0.0905 0.5803 1.0000
3.000 0.7624 0.00774 0.00270 -0.0892 0.5579 1.0000
3.250 0.7840 0.00794 0.00280 -0.0879 0.5353 1.0000
3.500 0.8052 0.00817 0.00292 -0.0865 0.5123 1.0000
3.750 0.8258 0.00842 0.00306 -0.0850 0.4903 1.0000
4.000 0.8468 0.00866 0.00320 -0.0836 0.4695 1.0000
4.250 0.8678 0.00890 0.00336 -0.0822 0.4513 1.0000
4.500 0.8890 0.00914 0.00353 -0.0809 0.4349 1.0000
4.750 0.9102 0.00938 0.00371 -0.0795 0.4196 1.0000
5.000 0.9315 0.00962 0.00389 -0.0782 0.4061 1.0000
5.250 0.9527 0.00987 0.00408 -0.0769 0.3928 1.0000
5.750 0.9955 0.01037 0.00447 -0.0744 0.3631 1.0000
6.000 1.0172 0.01062 0.00467 -0.0732 0.3477 1.0000
6.250 1.0396 0.01086 0.00488 -0.0722 0.3345 1.0000
6.500 1.0622 0.01110 0.00511 -0.0712 0.3232 1.0000
6.750 1.0843 0.01137 0.00535 -0.0701 0.3112 1.0000
7.000 1.1061 0.01167 0.00560 -0.0690 0.2981 1.0000
7.250 1.1282 0.01195 0.00586 -0.0680 0.2844 1.0000
7.500 1.1500 0.01226 0.00614 -0.0670 0.2694 1.0000
8.000 1.1915 0.01301 0.00678 -0.0646 0.2321 1.0000
8.250 1.2098 0.01354 0.00718 -0.0631 0.2069 1.0000
8.500 1.2265 0.01419 0.00766 -0.0614 0.1739 1.0000
8.750 1.2396 0.01506 0.00830 -0.0592 0.1373 1.0000
9.000 1.2523 0.01586 0.00896 -0.0568 0.1129 1.0000
9.250 1.2651 0.01664 0.00963 -0.0545 0.0932 1.0000
9.500 1.2771 0.01749 0.01036 -0.0521 0.0740 1.0000
9.750 1.2892 0.01834 0.01113 -0.0498 0.0616 1.0000
10.000 1.3022 0.01913 0.01190 -0.0477 0.0547 1.0000
10.250 1.3157 0.01989 0.01269 -0.0457 0.0502 1.0000
10.500 1.3278 0.02075 0.01356 -0.0437 0.0466 1.0000
10.750 1.3389 0.02168 0.01453 -0.0416 0.0437 1.0000
11.000 1.3523 0.02248 0.01539 -0.0398 0.0413 1.0000
11.250 1.3620 0.02354 0.01647 -0.0378 0.0391 1.0000
11.500 1.3683 0.02487 0.01785 -0.0355 0.0372 1.0000
11.750 1.3803 0.02583 0.01890 -0.0339 0.0357 1.0000
12.000 1.3904 0.02696 0.02009 -0.0323 0.0342 1.0000
12.250 1.3969 0.02839 0.02156 -0.0305 0.0327 1.0000
12.500 1.3965 0.03042 0.02365 -0.0282 0.0314 1.0000
12.750 1.4071 0.03164 0.02497 -0.0270 0.0304 1.0000
13.000 1.4147 0.03316 0.02658 -0.0257 0.0293 1.0000
13.250 1.4205 0.03486 0.02834 -0.0245 0.0283 1.0000
13.500 1.4237 0.03685 0.03040 -0.0233 0.0275 1.0000
13.750 1.4202 0.03955 0.03315 -0.0219 0.0267 1.0000
14.000 1.4195 0.04206 0.03576 -0.0208 0.0260 1.0000
14.250 1.4248 0.04410 0.03791 -0.0202 0.0253 1.0000
14.500 1.4281 0.04640 0.04031 -0.0196 0.0246 1.0000
14.750 1.4305 0.04885 0.04286 -0.0192 0.0239 1.0000
15.000 1.4317 0.05153 0.04561 -0.0190 0.0234 1.0000
15.250 1.4312 0.05449 0.04863 -0.0189 0.0228 1.0000
15.500 1.4268 0.05792 0.05213 -0.0189 0.0223 1.0000
15.750 1.4182 0.06181 0.05609 -0.0187 0.0218 1.0000
16.000 1.4190 0.06490 0.05930 -0.0190 0.0215 1.0000
16.250 1.4182 0.06822 0.06275 -0.0195 0.0211 1.0000
16.500 1.4164 0.07172 0.06636 -0.0201 0.0207 1.0000
16.750 1.4139 0.07535 0.07010 -0.0207 0.0204 1.0000
17.000 1.4111 0.07910 0.07395 -0.0215 0.0200 1.0000
17.250 1.4080 0.08293 0.07788 -0.0225 0.0196 1.0000
17.500 1.4047 0.08684 0.08187 -0.0235 0.0193 1.0000
17.750 1.4011 0.09080 0.08590 -0.0247 0.0190 1.0000
18.000 1.3972 0.09482 0.08998 -0.0258 0.0187 1.0000
18.250 1.3925 0.09879 0.09401 -0.0268 0.0183 1.0000
18.500 1.3866 0.10281 0.09811 -0.0276 0.0180 1.0000
18.750 1.3811 0.10741 0.10285 -0.0294 0.0178 1.0000
19.000 1.3755 0.11204 0.10761 -0.0313 0.0175 1.0000
19.250 1.3698 0.11669 0.11239 -0.0333 0.0173 1.0000
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