CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK Z AIRFOIL (clarkz-il) Reynolds number: 200,000 Max Cl/Cd: 72.15 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkz-il-200000-n5.txt Download as CSV file: xf-clarkz-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK Z 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3309 0.09910 0.09533 -0.0418 1.0000 0.0457
-9.250 -0.3279 0.09714 0.09342 -0.0407 1.0000 0.0464
-8.750 -0.3533 0.08562 0.08195 -0.0467 0.9955 0.0378
-8.500 -0.3388 0.08192 0.07825 -0.0503 0.9903 0.0374
-8.250 -0.3261 0.07713 0.07346 -0.0561 0.9840 0.0368
-8.000 -0.3151 0.07120 0.06751 -0.0643 0.9742 0.0364
-7.750 -0.3038 0.06382 0.06005 -0.0744 0.9638 0.0364
-7.500 -0.2924 0.05565 0.05170 -0.0838 0.9537 0.0364
-7.250 -0.2806 0.04754 0.04330 -0.0906 0.9447 0.0360
-7.000 -0.2747 0.03923 0.03448 -0.0941 0.9332 0.0357
-6.750 -0.2616 0.03289 0.02752 -0.0958 0.9253 0.0357
-6.500 -0.2446 0.02913 0.02326 -0.0958 0.9165 0.0359
-6.250 -0.2213 0.02641 0.02005 -0.0962 0.9104 0.0367
-6.000 -0.1999 0.02442 0.01763 -0.0956 0.9017 0.0373
-5.750 -0.1731 0.02271 0.01555 -0.0957 0.8960 0.0377
-5.500 -0.1493 0.02145 0.01400 -0.0951 0.8873 0.0379
-5.250 -0.1219 0.02031 0.01259 -0.0951 0.8808 0.0383
-5.000 -0.0966 0.01929 0.01147 -0.0947 0.8725 0.0387
-4.750 -0.0693 0.01847 0.01055 -0.0946 0.8652 0.0392
-4.500 -0.0430 0.01778 0.00978 -0.0942 0.8569 0.0397
-4.250 -0.0157 0.01714 0.00904 -0.0940 0.8489 0.0403
-4.000 0.0108 0.01660 0.00843 -0.0936 0.8400 0.0412
-3.750 0.0382 0.01609 0.00782 -0.0933 0.8316 0.0425
-3.500 0.0646 0.01562 0.00727 -0.0929 0.8220 0.0435
-3.250 0.0921 0.01515 0.00669 -0.0925 0.8137 0.0444
-3.000 0.1178 0.01466 0.00619 -0.0920 0.8035 0.0452
-2.750 0.1446 0.01425 0.00577 -0.0917 0.7947 0.0463
-2.500 0.1710 0.01393 0.00542 -0.0913 0.7847 0.0477
-2.250 0.1977 0.01364 0.00509 -0.0909 0.7751 0.0494
-2.000 0.2247 0.01340 0.00476 -0.0905 0.7654 0.0515
-1.750 0.2510 0.01314 0.00451 -0.0901 0.7550 0.0549
-1.500 0.2780 0.01294 0.00427 -0.0897 0.7453 0.0595
-1.250 0.3045 0.01272 0.00406 -0.0893 0.7347 0.0662
-1.000 0.3312 0.01252 0.00388 -0.0889 0.7245 0.0804
-0.750 0.3579 0.01233 0.00375 -0.0886 0.7146 0.1090
-0.500 0.3841 0.01213 0.00368 -0.0882 0.7038 0.1478
-0.250 0.4103 0.01193 0.00361 -0.0879 0.6935 0.1981
0.000 0.4351 0.01151 0.00356 -0.0874 0.6829 0.3191
0.250 0.4509 0.01035 0.00368 -0.0850 0.6726 0.6923
0.500 0.5066 0.00996 0.00376 -0.0895 0.6611 0.9793
0.750 0.5475 0.01003 0.00369 -0.0922 0.6489 1.0000
1.000 0.5718 0.01013 0.00368 -0.0914 0.6369 1.0000
1.250 0.5961 0.01024 0.00368 -0.0906 0.6251 1.0000
1.500 0.6205 0.01037 0.00369 -0.0897 0.6132 1.0000
1.750 0.6448 0.01050 0.00372 -0.0889 0.6005 1.0000
2.000 0.6693 0.01064 0.00377 -0.0882 0.5877 1.0000
2.250 0.6937 0.01079 0.00383 -0.0874 0.5747 1.0000
2.500 0.7180 0.01095 0.00390 -0.0866 0.5618 1.0000
2.750 0.7423 0.01113 0.00399 -0.0858 0.5486 1.0000
3.000 0.7666 0.01131 0.00409 -0.0850 0.5348 1.0000
3.250 0.7910 0.01150 0.00421 -0.0843 0.5211 1.0000
3.500 0.8152 0.01170 0.00435 -0.0836 0.5078 1.0000
3.750 0.8393 0.01192 0.00449 -0.0828 0.4944 1.0000
4.000 0.8633 0.01216 0.00465 -0.0820 0.4813 1.0000
4.250 0.8869 0.01242 0.00483 -0.0812 0.4672 1.0000
4.500 0.9104 0.01268 0.00502 -0.0804 0.4522 1.0000
4.750 0.9335 0.01296 0.00523 -0.0795 0.4366 1.0000
5.000 0.9564 0.01326 0.00546 -0.0786 0.4205 1.0000
5.250 0.9791 0.01357 0.00570 -0.0777 0.4049 1.0000
5.500 1.0016 0.01389 0.00595 -0.0767 0.3891 1.0000
5.750 1.0240 0.01422 0.00623 -0.0758 0.3739 1.0000
6.000 1.0466 0.01455 0.00652 -0.0749 0.3604 1.0000
6.250 1.0690 0.01489 0.00682 -0.0741 0.3483 1.0000
6.500 1.0909 0.01525 0.00715 -0.0731 0.3361 1.0000
6.750 1.1132 0.01559 0.00749 -0.0722 0.3240 1.0000
7.000 1.1351 0.01595 0.00784 -0.0713 0.3120 1.0000
7.250 1.1561 0.01634 0.00822 -0.0702 0.2992 1.0000
7.500 1.1765 0.01676 0.00862 -0.0691 0.2854 1.0000
7.750 1.1962 0.01721 0.00904 -0.0678 0.2706 1.0000
8.000 1.2152 0.01769 0.00949 -0.0665 0.2553 1.0000
8.250 1.2334 0.01820 0.00998 -0.0651 0.2389 1.0000
8.500 1.2501 0.01878 0.01052 -0.0635 0.2209 1.0000
8.750 1.2639 0.01944 0.01110 -0.0615 0.2018 1.0000
9.000 1.2760 0.02021 0.01179 -0.0592 0.1828 1.0000
9.250 1.2882 0.02103 0.01255 -0.0571 0.1651 1.0000
9.500 1.2997 0.02191 0.01337 -0.0550 0.1503 1.0000
9.750 1.3108 0.02284 0.01427 -0.0530 0.1387 1.0000
10.000 1.3225 0.02376 0.01519 -0.0511 0.1295 1.0000
10.250 1.3337 0.02473 0.01619 -0.0492 0.1228 1.0000
10.500 1.3446 0.02574 0.01723 -0.0475 0.1172 1.0000
10.750 1.3535 0.02692 0.01842 -0.0456 0.1125 1.0000
11.000 1.3649 0.02796 0.01953 -0.0441 0.1081 1.0000
11.250 1.3739 0.02921 0.02081 -0.0425 0.1037 1.0000
11.500 1.3804 0.03067 0.02229 -0.0408 0.1000 1.0000
11.750 1.3914 0.03184 0.02356 -0.0395 0.0966 1.0000
12.000 1.4002 0.03322 0.02501 -0.0383 0.0935 1.0000
12.250 1.4071 0.03479 0.02663 -0.0370 0.0908 1.0000
12.500 1.4111 0.03664 0.02851 -0.0357 0.0883 1.0000
12.750 1.4202 0.03811 0.03011 -0.0347 0.0860 1.0000
13.000 1.4284 0.03971 0.03182 -0.0338 0.0837 1.0000
13.250 1.4349 0.04147 0.03368 -0.0329 0.0816 1.0000
13.500 1.4395 0.04346 0.03575 -0.0321 0.0795 1.0000
13.750 1.4414 0.04576 0.03809 -0.0313 0.0774 1.0000
14.000 1.4470 0.04775 0.04020 -0.0308 0.0752 1.0000
14.250 1.4532 0.04973 0.04232 -0.0303 0.0728 1.0000
14.500 1.4576 0.05195 0.04466 -0.0299 0.0706 1.0000
14.750 1.4596 0.05450 0.04729 -0.0297 0.0684 1.0000
15.000 1.4586 0.05746 0.05030 -0.0297 0.0663 1.0000
15.250 1.4644 0.05970 0.05272 -0.0296 0.0635 1.0000
15.500 1.4668 0.06240 0.05556 -0.0297 0.0608 1.0000
15.750 1.4662 0.06556 0.05880 -0.0300 0.0584 1.0000
16.000 1.4658 0.06876 0.06211 -0.0304 0.0559 1.0000
16.250 1.4667 0.07182 0.06531 -0.0309 0.0526 1.0000
16.500 1.4630 0.07561 0.06919 -0.0316 0.0495 1.0000
16.750 1.4612 0.07918 0.07288 -0.0324 0.0456 1.0000
17.000 1.4550 0.08347 0.07725 -0.0335 0.0419 1.0000
17.250 1.4488 0.08779 0.08166 -0.0346 0.0373 1.0000
17.500 1.4399 0.09259 0.08654 -0.0360 0.0335 1.0000
17.750 1.4291 0.09780 0.09182 -0.0377 0.0304 1.0000
18.000 1.4175 0.10322 0.09733 -0.0396 0.0279 1.0000
18.250 1.4048 0.10890 0.10310 -0.0418 0.0263 1.0000
18.500 1.3927 0.11458 0.10889 -0.0440 0.0251 1.0000
18.750 1.3801 0.12047 0.11489 -0.0465 0.0241 1.0000
19.000 1.3668 0.12661 0.12114 -0.0493 0.0233 1.0000
19.250 1.3528 0.13302 0.12766 -0.0524 0.0227 1.0000
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