CLARK W AIRFOIL (clarkw-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK W AIRFOIL (clarkw-il) Reynolds number: 200,000 Max Cl/Cd: 73.54 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkw-il-200000.txt Download as CSV file: xf-clarkw-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.4029 0.08899 0.08552 -0.0330 1.0000 0.0809
-8.000 -0.4222 0.08756 0.08417 -0.0299 1.0000 0.0820
-7.750 -0.4484 0.08639 0.08309 -0.0262 1.0000 0.0826
-7.500 -0.4725 0.08451 0.08128 -0.0244 1.0000 0.0837
-7.250 -0.4663 0.07266 0.06929 -0.0442 0.9916 0.0885
-7.000 -0.4441 0.07027 0.06690 -0.0446 0.9880 0.0896
-6.750 -0.4590 0.04211 0.03741 -0.0641 0.9761 0.0657
-6.500 -0.4330 0.03730 0.03227 -0.0664 0.9724 0.0617
-6.250 -0.4100 0.03233 0.02670 -0.0681 0.9680 0.0602
-6.000 -0.3873 0.02824 0.02192 -0.0685 0.9624 0.0587
-5.750 -0.3549 0.02564 0.01879 -0.0700 0.9591 0.0584
-5.500 -0.3180 0.02392 0.01675 -0.0721 0.9569 0.0588
-5.250 -0.2919 0.02282 0.01545 -0.0719 0.9507 0.0596
-5.000 -0.2582 0.02186 0.01431 -0.0732 0.9464 0.0614
-4.750 -0.2203 0.02087 0.01313 -0.0751 0.9437 0.0629
-4.500 -0.1801 0.01997 0.01207 -0.0775 0.9416 0.0641
-4.250 -0.1564 0.01906 0.01114 -0.0767 0.9342 0.0657
-4.000 -0.1201 0.01832 0.01044 -0.0784 0.9304 0.0684
-3.750 -0.0798 0.01770 0.00980 -0.0808 0.9278 0.0726
-3.500 -0.0366 0.01694 0.00909 -0.0838 0.9259 0.0795
-3.250 -0.0120 0.01651 0.00865 -0.0829 0.9166 0.0879
-3.000 0.0275 0.01552 0.00789 -0.0850 0.9129 0.1231
-2.750 0.0680 0.01487 0.00741 -0.0873 0.9102 0.1679
-2.500 0.0911 0.01465 0.00728 -0.0862 0.9006 0.1956
-2.250 0.1270 0.01423 0.00699 -0.0875 0.8965 0.2323
-2.000 0.1559 0.01400 0.00685 -0.0875 0.8896 0.2680
-1.750 0.1860 0.01375 0.00668 -0.0876 0.8828 0.3034
-1.500 0.2208 0.01345 0.00641 -0.0885 0.8786 0.3400
-1.250 0.2445 0.01332 0.00636 -0.0874 0.8688 0.3677
-1.000 0.2766 0.01295 0.00604 -0.0878 0.8634 0.3957
-0.750 0.3016 0.01275 0.00590 -0.0869 0.8539 0.4208
-0.500 0.3316 0.01231 0.00558 -0.0869 0.8475 0.4507
-0.250 0.3552 0.01196 0.00543 -0.0858 0.8375 0.4902
0.000 0.4029 0.01067 0.00548 -0.0883 0.8322 0.9355
0.250 0.4919 0.01051 0.00519 -0.1006 0.8257 1.0000
0.500 0.5180 0.01044 0.00501 -0.0998 0.8152 1.0000
0.750 0.5417 0.01044 0.00493 -0.0987 0.8028 1.0000
1.000 0.5664 0.01042 0.00483 -0.0978 0.7909 1.0000
1.250 0.5919 0.01040 0.00471 -0.0969 0.7790 1.0000
1.500 0.6167 0.01039 0.00462 -0.0959 0.7660 1.0000
1.750 0.6402 0.01042 0.00459 -0.0948 0.7514 1.0000
2.000 0.6639 0.01046 0.00455 -0.0936 0.7363 1.0000
2.250 0.6876 0.01050 0.00453 -0.0925 0.7205 1.0000
2.500 0.7113 0.01056 0.00451 -0.0914 0.7036 1.0000
2.750 0.7347 0.01065 0.00451 -0.0902 0.6860 1.0000
3.000 0.7576 0.01076 0.00454 -0.0889 0.6670 1.0000
3.250 0.7797 0.01090 0.00461 -0.0876 0.6459 1.0000
3.500 0.8019 0.01107 0.00467 -0.0862 0.6246 1.0000
3.750 0.8240 0.01129 0.00476 -0.0848 0.6040 1.0000
4.000 0.8451 0.01152 0.00492 -0.0833 0.5818 1.0000
4.250 0.8663 0.01178 0.00508 -0.0819 0.5607 1.0000
4.500 0.8876 0.01208 0.00526 -0.0804 0.5411 1.0000
4.750 0.9088 0.01240 0.00548 -0.0790 0.5222 1.0000
5.000 0.9296 0.01271 0.00572 -0.0776 0.5028 1.0000
5.250 0.9506 0.01304 0.00598 -0.0762 0.4846 1.0000
5.500 0.9717 0.01338 0.00625 -0.0749 0.4679 1.0000
5.750 0.9929 0.01373 0.00655 -0.0736 0.4521 1.0000
6.000 1.0146 0.01410 0.00686 -0.0724 0.4381 1.0000
6.250 1.0367 0.01449 0.00719 -0.0713 0.4255 1.0000
6.500 1.0576 0.01485 0.00752 -0.0700 0.4108 1.0000
6.750 1.0773 0.01519 0.00782 -0.0685 0.3941 1.0000
7.000 1.0968 0.01552 0.00813 -0.0670 0.3777 1.0000
7.250 1.1169 0.01585 0.00848 -0.0656 0.3634 1.0000
7.500 1.1371 0.01618 0.00885 -0.0642 0.3494 1.0000
7.750 1.1568 0.01653 0.00923 -0.0628 0.3352 1.0000
8.000 1.1758 0.01690 0.00961 -0.0613 0.3203 1.0000
8.250 1.1940 0.01728 0.01001 -0.0597 0.3044 1.0000
8.500 1.2110 0.01770 0.01045 -0.0579 0.2867 1.0000
8.750 1.2263 0.01819 0.01091 -0.0558 0.2668 1.0000
9.000 1.2407 0.01871 0.01142 -0.0537 0.2415 1.0000
9.250 1.2501 0.01943 0.01202 -0.0508 0.2104 1.0000
9.500 1.2556 0.02047 0.01286 -0.0475 0.1704 1.0000
9.750 1.2568 0.02193 0.01404 -0.0439 0.1350 1.0000
10.000 1.2581 0.02349 0.01543 -0.0405 0.1115 1.0000
10.250 1.2597 0.02510 0.01693 -0.0373 0.0966 1.0000
10.500 1.2654 0.02649 0.01832 -0.0348 0.0861 1.0000
10.750 1.2711 0.02793 0.01978 -0.0324 0.0787 1.0000
11.000 1.2745 0.02956 0.02139 -0.0300 0.0733 1.0000
11.250 1.2814 0.03104 0.02295 -0.0280 0.0688 1.0000
11.500 1.2876 0.03258 0.02453 -0.0262 0.0650 1.0000
11.750 1.2886 0.03465 0.02656 -0.0240 0.0618 1.0000
12.000 1.2971 0.03615 0.02819 -0.0226 0.0589 1.0000
12.250 1.3033 0.03784 0.02995 -0.0211 0.0562 1.0000
12.500 1.3077 0.03979 0.03189 -0.0195 0.0540 1.0000
12.750 1.3140 0.04173 0.03387 -0.0179 0.0519 1.0000
13.000 1.3209 0.04351 0.03580 -0.0167 0.0498 1.0000
13.250 1.3274 0.04536 0.03772 -0.0156 0.0479 1.0000
13.500 1.3342 0.04724 0.03959 -0.0145 0.0461 1.0000
13.750 1.3458 0.04915 0.04149 -0.0130 0.0444 1.0000
14.000 1.3507 0.05125 0.04380 -0.0120 0.0433 1.0000
14.250 1.3559 0.05341 0.04611 -0.0110 0.0419 1.0000
14.500 1.3600 0.05565 0.04848 -0.0102 0.0407 1.0000
14.750 1.3646 0.05786 0.05076 -0.0095 0.0395 1.0000
15.000 1.3758 0.05977 0.05262 -0.0086 0.0381 1.0000
15.250 1.3800 0.06264 0.05565 -0.0076 0.0372 1.0000
15.500 1.3752 0.06588 0.05915 -0.0072 0.0367 1.0000
15.750 1.3695 0.06938 0.06289 -0.0070 0.0362 1.0000
16.000 1.3628 0.07316 0.06690 -0.0071 0.0357 1.0000
16.250 1.3546 0.07721 0.07116 -0.0074 0.0352 1.0000
16.500 1.3454 0.08151 0.07567 -0.0081 0.0347 1.0000
16.750 1.3357 0.08603 0.08037 -0.0092 0.0343 1.0000
17.000 1.3261 0.09068 0.08520 -0.0105 0.0338 1.0000
17.250 1.3169 0.09536 0.09003 -0.0121 0.0334 1.0000
17.500 1.3047 0.10068 0.09552 -0.0142 0.0331 1.0000
17.750 1.2915 0.10637 0.10137 -0.0168 0.0328 1.0000
18.000 1.2755 0.11281 0.10800 -0.0200 0.0326 1.0000
18.250 1.2510 0.12121 0.11664 -0.0249 0.0327 1.0000
18.500 1.0064 0.19640 0.19267 -0.0710 0.0446 1.0000
18.750 1.0757 0.17377 0.17008 -0.0600 0.0373 1.0000
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