CLARK W AIRFOIL (clarkw-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: CLARK W AIRFOIL (clarkw-il) Reynolds number: 200,000 Max Cl/Cd: 69.72 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkw-il-200000-n5.txt Download as CSV file: xf-clarkw-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4315 0.08999 0.08608 -0.0467 1.0000 0.0329
-10.000 -0.4457 0.08473 0.08087 -0.0481 1.0000 0.0330
-9.750 -0.4699 0.07865 0.07487 -0.0494 1.0000 0.0330
-9.250 -0.6085 0.03918 0.03423 -0.0776 0.9833 0.0328
-9.000 -0.5964 0.03507 0.02948 -0.0792 0.9763 0.0333
-8.750 -0.5741 0.03197 0.02599 -0.0809 0.9728 0.0337
-8.500 -0.5537 0.02990 0.02369 -0.0811 0.9673 0.0340
-8.250 -0.5279 0.02815 0.02172 -0.0820 0.9633 0.0345
-8.000 -0.4986 0.02658 0.01993 -0.0834 0.9606 0.0349
-7.750 -0.4726 0.02535 0.01852 -0.0838 0.9563 0.0356
-7.500 -0.4463 0.02422 0.01721 -0.0841 0.9514 0.0363
-7.250 -0.4163 0.02306 0.01584 -0.0851 0.9482 0.0371
-7.000 -0.3851 0.02192 0.01450 -0.0862 0.9457 0.0377
-6.750 -0.3607 0.02101 0.01343 -0.0857 0.9397 0.0381
-6.500 -0.3325 0.02013 0.01240 -0.0860 0.9351 0.0386
-6.000 -0.2706 0.01858 0.01059 -0.0875 0.9287 0.0397
-5.750 -0.2473 0.01788 0.00986 -0.0866 0.9216 0.0403
-5.500 -0.2183 0.01718 0.00914 -0.0870 0.9173 0.0413
-5.250 -0.1870 0.01661 0.00854 -0.0878 0.9141 0.0426
-5.000 -0.1626 0.01618 0.00807 -0.0871 0.9071 0.0438
-4.750 -0.1339 0.01571 0.00754 -0.0872 0.9020 0.0450
-4.500 -0.1030 0.01525 0.00701 -0.0877 0.8982 0.0462
-4.250 -0.0780 0.01490 0.00661 -0.0871 0.8910 0.0475
-4.000 -0.0494 0.01448 0.00618 -0.0871 0.8855 0.0496
-3.750 -0.0194 0.01411 0.00578 -0.0874 0.8809 0.0528
-3.500 0.0061 0.01381 0.00550 -0.0869 0.8729 0.0576
-3.250 0.0360 0.01341 0.00514 -0.0871 0.8667 0.0712
-3.000 0.0617 0.01310 0.00490 -0.0865 0.8565 0.0920
-2.750 0.0908 0.01279 0.00461 -0.0865 0.8486 0.1124
-2.500 0.1172 0.01258 0.00442 -0.0861 0.8390 0.1297
-2.250 0.1452 0.01233 0.00423 -0.0860 0.8315 0.1521
-2.000 0.1719 0.01214 0.00409 -0.0856 0.8224 0.1749
-1.750 0.1991 0.01193 0.00398 -0.0853 0.8140 0.2079
-1.500 0.2260 0.01176 0.00391 -0.0850 0.8049 0.2422
-1.250 0.2527 0.01164 0.00385 -0.0847 0.7956 0.2741
-1.000 0.2802 0.01153 0.00378 -0.0844 0.7866 0.3019
-0.750 0.3066 0.01146 0.00374 -0.0839 0.7762 0.3261
-0.500 0.3338 0.01138 0.00367 -0.0836 0.7667 0.3468
-0.250 0.3602 0.01131 0.00361 -0.0831 0.7558 0.3652
0.000 0.3865 0.01123 0.00356 -0.0827 0.7448 0.3847
0.250 0.4129 0.01114 0.00349 -0.0822 0.7336 0.4069
0.500 0.4384 0.01100 0.00343 -0.0816 0.7215 0.4387
0.750 0.4616 0.01067 0.00339 -0.0805 0.7086 0.5115
1.250 0.5506 0.00996 0.00366 -0.0861 0.6794 0.9779
1.500 0.5951 0.01005 0.00364 -0.0896 0.6621 0.9950
1.750 0.6279 0.01015 0.00363 -0.0906 0.6445 1.0000
2.000 0.6510 0.01028 0.00365 -0.0895 0.6268 1.0000
2.250 0.6738 0.01043 0.00369 -0.0883 0.6084 1.0000
2.500 0.6962 0.01060 0.00376 -0.0871 0.5893 1.0000
2.750 0.7184 0.01078 0.00384 -0.0859 0.5696 1.0000
3.000 0.7402 0.01098 0.00394 -0.0846 0.5503 1.0000
3.250 0.7617 0.01121 0.00406 -0.0833 0.5309 1.0000
3.500 0.7829 0.01145 0.00420 -0.0819 0.5120 1.0000
3.750 0.8040 0.01170 0.00435 -0.0805 0.4944 1.0000
4.000 0.8254 0.01196 0.00454 -0.0791 0.4785 1.0000
4.250 0.8468 0.01222 0.00473 -0.0778 0.4632 1.0000
4.500 0.8683 0.01249 0.00494 -0.0766 0.4487 1.0000
4.750 0.8899 0.01277 0.00518 -0.0753 0.4347 1.0000
5.000 0.9113 0.01307 0.00542 -0.0741 0.4204 1.0000
5.250 0.9325 0.01338 0.00567 -0.0728 0.4059 1.0000
5.500 0.9538 0.01369 0.00594 -0.0716 0.3924 1.0000
5.750 0.9751 0.01402 0.00622 -0.0704 0.3799 1.0000
6.000 0.9968 0.01432 0.00651 -0.0693 0.3667 1.0000
6.250 1.0187 0.01463 0.00681 -0.0682 0.3552 1.0000
6.500 1.0402 0.01495 0.00714 -0.0671 0.3445 1.0000
6.750 1.0605 0.01531 0.00746 -0.0658 0.3289 1.0000
7.000 1.0800 0.01569 0.00780 -0.0643 0.3099 1.0000
7.250 1.0994 0.01610 0.00817 -0.0629 0.2920 1.0000
7.500 1.1193 0.01649 0.00855 -0.0616 0.2773 1.0000
7.750 1.1387 0.01691 0.00895 -0.0603 0.2621 1.0000
8.000 1.1575 0.01735 0.00938 -0.0588 0.2461 1.0000
8.250 1.1751 0.01786 0.00986 -0.0572 0.2276 1.0000
8.500 1.1906 0.01845 0.01038 -0.0553 0.2065 1.0000
8.750 1.2043 0.01911 0.01095 -0.0532 0.1815 1.0000
9.000 1.2159 0.01991 0.01164 -0.0508 0.1552 1.0000
9.250 1.2265 0.02083 0.01244 -0.0484 0.1332 1.0000
9.500 1.2375 0.02176 0.01330 -0.0461 0.1163 1.0000
9.750 1.2485 0.02271 0.01421 -0.0439 0.1024 1.0000
10.000 1.2594 0.02368 0.01516 -0.0418 0.0902 1.0000
10.250 1.2699 0.02470 0.01617 -0.0398 0.0795 1.0000
10.500 1.2793 0.02580 0.01727 -0.0377 0.0707 1.0000
10.750 1.2894 0.02688 0.01838 -0.0358 0.0640 1.0000
11.000 1.2978 0.02811 0.01963 -0.0339 0.0591 1.0000
11.250 1.3065 0.02934 0.02092 -0.0321 0.0549 1.0000
11.500 1.3123 0.03083 0.02244 -0.0302 0.0516 1.0000
11.750 1.3206 0.03218 0.02389 -0.0286 0.0489 1.0000
12.000 1.3273 0.03370 0.02550 -0.0271 0.0463 1.0000
12.250 1.3312 0.03549 0.02734 -0.0256 0.0441 1.0000
12.500 1.3351 0.03736 0.02929 -0.0241 0.0423 1.0000
12.750 1.3406 0.03916 0.03121 -0.0230 0.0404 1.0000
13.000 1.3443 0.04116 0.03331 -0.0219 0.0387 1.0000
13.250 1.3456 0.04347 0.03569 -0.0209 0.0372 1.0000
13.500 1.3442 0.04612 0.03842 -0.0201 0.0360 1.0000
13.750 1.3469 0.04844 0.04089 -0.0194 0.0347 1.0000
14.000 1.3481 0.05099 0.04356 -0.0189 0.0335 1.0000
14.250 1.3483 0.05375 0.04643 -0.0186 0.0323 1.0000
14.500 1.3469 0.05679 0.04956 -0.0185 0.0313 1.0000
14.750 1.3427 0.06024 0.05307 -0.0186 0.0304 1.0000
15.000 1.3410 0.06350 0.05646 -0.0188 0.0296 1.0000
15.250 1.3399 0.06679 0.05989 -0.0191 0.0286 1.0000
15.500 1.3376 0.07029 0.06351 -0.0195 0.0278 1.0000
15.750 1.3346 0.07395 0.06731 -0.0202 0.0270 1.0000
16.000 1.3311 0.07779 0.07124 -0.0210 0.0263 1.0000
16.250 1.3268 0.08181 0.07536 -0.0220 0.0257 1.0000
16.500 1.3212 0.08600 0.07960 -0.0231 0.0252 1.0000
16.750 1.3175 0.09001 0.08375 -0.0241 0.0246 1.0000
17.000 1.3138 0.09411 0.08801 -0.0253 0.0239 1.0000
17.250 1.3094 0.09839 0.09242 -0.0266 0.0232 1.0000
17.500 1.3047 0.10277 0.09692 -0.0282 0.0227 1.0000
17.750 1.2997 0.10723 0.10149 -0.0298 0.0221 1.0000
18.000 1.2948 0.11174 0.10611 -0.0316 0.0217 1.0000
18.250 1.2899 0.11628 0.11073 -0.0335 0.0213 1.0000
18.500 1.2853 0.12077 0.11529 -0.0354 0.0209 1.0000
18.750 1.2811 0.12516 0.11977 -0.0373 0.0206 1.0000
19.000 1.2748 0.13018 0.12496 -0.0397 0.0202 1.0000
19.250 1.2679 0.13541 0.13036 -0.0423 0.0198 1.0000
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