CLARK Z AIRFOIL (clarkz-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK Z AIRFOIL (clarkz-il) Reynolds number: 500,000 Max Cl/Cd: 100.92 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkz-il-500000.txt Download as CSV file: xf-clarkz-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3321 0.09602 0.09363 -0.0409 1.0000 0.0346
-9.250 -0.3347 0.09399 0.09164 -0.0398 1.0000 0.0350
-9.000 -0.3440 0.09238 0.09009 -0.0375 1.0000 0.0354
-8.750 -0.3365 0.08894 0.08665 -0.0403 0.9981 0.0363
-8.500 -0.3426 0.07341 0.07111 -0.0661 0.9870 0.0390
-8.250 -0.3235 0.07050 0.06820 -0.0681 0.9847 0.0393
-8.000 -0.2998 0.06730 0.06499 -0.0725 0.9827 0.0397
-7.750 -0.2798 0.06390 0.06156 -0.0770 0.9767 0.0402
-7.500 -0.2347 0.03440 0.03167 -0.0965 0.9486 0.0453
-7.250 -0.2195 0.03192 0.02923 -0.0963 0.9417 0.0458
-7.000 -0.2051 0.03027 0.02757 -0.0957 0.9319 0.0462
-6.750 -0.1895 0.02842 0.02565 -0.0955 0.9238 0.0467
-6.500 -0.1752 0.02629 0.02345 -0.0953 0.9135 0.0475
-6.250 -0.1605 0.02356 0.02056 -0.0955 0.9046 0.0488
-6.000 -0.1845 0.02181 0.01668 -0.0984 0.9117 0.0391
-5.750 -0.1610 0.02050 0.01514 -0.0977 0.9035 0.0390
-5.500 -0.1375 0.01891 0.01331 -0.0970 0.8953 0.0390
-5.250 -0.1127 0.01782 0.01203 -0.0964 0.8868 0.0389
-5.000 -0.0876 0.01665 0.01066 -0.0958 0.8784 0.0389
-4.750 -0.0625 0.01541 0.00926 -0.0952 0.8694 0.0391
-4.500 -0.0366 0.01433 0.00803 -0.0947 0.8610 0.0393
-4.250 -0.0108 0.01349 0.00712 -0.0943 0.8516 0.0397
-3.750 0.0421 0.01239 0.00592 -0.0934 0.8334 0.0408
-3.500 0.0690 0.01202 0.00548 -0.0931 0.8246 0.0418
-3.250 0.0957 0.01166 0.00508 -0.0927 0.8146 0.0427
-3.000 0.1224 0.01130 0.00466 -0.0923 0.8053 0.0435
-2.750 0.1493 0.01099 0.00427 -0.0918 0.7957 0.0443
-2.500 0.1762 0.01074 0.00397 -0.0915 0.7859 0.0450
-2.250 0.2023 0.01029 0.00348 -0.0910 0.7768 0.0464
-2.000 0.2290 0.01003 0.00323 -0.0906 0.7667 0.0480
-1.750 0.2561 0.00986 0.00301 -0.0903 0.7574 0.0500
-1.500 0.2833 0.00973 0.00284 -0.0900 0.7475 0.0524
-1.250 0.3101 0.00950 0.00261 -0.0897 0.7379 0.0572
-1.000 0.3372 0.00934 0.00243 -0.0893 0.7285 0.0647
-0.750 0.3638 0.00906 0.00231 -0.0890 0.7181 0.1034
-0.500 0.3903 0.00885 0.00225 -0.0887 0.7084 0.1598
-0.250 0.4165 0.00860 0.00221 -0.0884 0.6981 0.2355
0.000 0.4403 0.00796 0.00221 -0.0879 0.6879 0.4495
0.250 0.4588 0.00714 0.00227 -0.0860 0.6780 0.7404
0.500 0.4825 0.00681 0.00240 -0.0842 0.6673 0.9238
0.750 0.5407 0.00688 0.00242 -0.0904 0.6553 0.9890
1.000 0.5867 0.00697 0.00239 -0.0943 0.6430 1.0000
1.250 0.6114 0.00706 0.00240 -0.0936 0.6311 1.0000
1.500 0.6361 0.00715 0.00241 -0.0928 0.6187 1.0000
1.750 0.6606 0.00726 0.00244 -0.0920 0.6061 1.0000
2.000 0.6849 0.00738 0.00248 -0.0912 0.5935 1.0000
2.500 0.7334 0.00764 0.00258 -0.0896 0.5659 1.0000
2.750 0.7576 0.00778 0.00266 -0.0888 0.5517 1.0000
3.000 0.7818 0.00793 0.00274 -0.0880 0.5369 1.0000
3.250 0.8056 0.00811 0.00283 -0.0871 0.5200 1.0000
3.500 0.8292 0.00832 0.00293 -0.0862 0.5017 1.0000
3.750 0.8530 0.00852 0.00305 -0.0854 0.4847 1.0000
4.000 0.8772 0.00873 0.00318 -0.0846 0.4688 1.0000
4.250 0.9011 0.00896 0.00333 -0.0839 0.4522 1.0000
4.500 0.9252 0.00919 0.00348 -0.0831 0.4362 1.0000
4.750 0.9494 0.00943 0.00364 -0.0824 0.4212 1.0000
5.000 0.9737 0.00966 0.00382 -0.0818 0.4071 1.0000
5.250 0.9981 0.00989 0.00401 -0.0811 0.3946 1.0000
5.500 1.0222 0.01015 0.00420 -0.0805 0.3821 1.0000
5.750 1.0463 0.01040 0.00441 -0.0798 0.3698 1.0000
6.000 1.0710 0.01062 0.00462 -0.0793 0.3585 1.0000
6.250 1.0951 0.01088 0.00484 -0.0786 0.3474 1.0000
6.500 1.1186 0.01117 0.00509 -0.0779 0.3355 1.0000
6.750 1.1424 0.01144 0.00533 -0.0773 0.3230 1.0000
7.000 1.1661 0.01172 0.00558 -0.0766 0.3105 1.0000
7.250 1.1894 0.01201 0.00585 -0.0759 0.2981 1.0000
7.500 1.2121 0.01234 0.00614 -0.0751 0.2847 1.0000
7.750 1.2342 0.01270 0.00645 -0.0742 0.2698 1.0000
8.000 1.2558 0.01309 0.00679 -0.0732 0.2525 1.0000
8.250 1.2758 0.01357 0.00718 -0.0721 0.2313 1.0000
8.500 1.2940 0.01416 0.00764 -0.0706 0.2056 1.0000
8.750 1.3093 0.01492 0.00822 -0.0688 0.1753 1.0000
9.000 1.3226 0.01574 0.00887 -0.0667 0.1485 1.0000
9.250 1.3350 0.01653 0.00954 -0.0644 0.1300 1.0000
9.500 1.3492 0.01722 0.01018 -0.0624 0.1188 1.0000
9.750 1.3639 0.01789 0.01083 -0.0605 0.1112 1.0000
10.000 1.3782 0.01859 0.01151 -0.0586 0.1054 1.0000
10.250 1.3918 0.01933 0.01227 -0.0568 0.1009 1.0000
10.500 1.4076 0.01995 0.01294 -0.0552 0.0977 1.0000
10.750 1.4212 0.02072 0.01372 -0.0535 0.0942 1.0000
11.000 1.4311 0.02172 0.01473 -0.0515 0.0906 1.0000
11.250 1.4462 0.02244 0.01551 -0.0501 0.0883 1.0000
11.500 1.4608 0.02319 0.01633 -0.0488 0.0861 1.0000
11.750 1.4736 0.02409 0.01728 -0.0473 0.0839 1.0000
12.000 1.4840 0.02517 0.01839 -0.0457 0.0816 1.0000
12.250 1.4902 0.02659 0.01985 -0.0438 0.0791 1.0000
12.500 1.5045 0.02748 0.02082 -0.0428 0.0774 1.0000
12.750 1.5190 0.02835 0.02177 -0.0418 0.0751 1.0000
13.000 1.5308 0.02945 0.02292 -0.0408 0.0728 1.0000
13.250 1.5393 0.03085 0.02436 -0.0396 0.0705 1.0000
13.500 1.5444 0.03259 0.02615 -0.0382 0.0682 1.0000
13.750 1.5592 0.03354 0.02720 -0.0376 0.0662 1.0000
14.000 1.5713 0.03472 0.02845 -0.0369 0.0635 1.0000
14.250 1.5787 0.03637 0.03012 -0.0360 0.0604 1.0000
14.500 1.5890 0.03779 0.03162 -0.0353 0.0570 1.0000
14.750 1.5968 0.03947 0.03331 -0.0347 0.0521 1.0000
15.000 1.6026 0.04137 0.03523 -0.0340 0.0455 1.0000
15.250 1.6014 0.04404 0.03788 -0.0333 0.0374 1.0000
15.500 1.5961 0.04726 0.04109 -0.0327 0.0305 1.0000
15.750 1.5890 0.05080 0.04466 -0.0322 0.0268 1.0000
16.000 1.5825 0.05442 0.04835 -0.0321 0.0247 1.0000
16.250 1.5742 0.05839 0.05239 -0.0321 0.0233 1.0000
16.500 1.5683 0.06217 0.05630 -0.0324 0.0224 1.0000
16.750 1.5607 0.06628 0.06051 -0.0328 0.0216 1.0000
17.000 1.5513 0.07076 0.06509 -0.0335 0.0210 1.0000
17.250 1.5399 0.07561 0.07004 -0.0344 0.0205 1.0000
17.500 1.5261 0.08091 0.07545 -0.0356 0.0200 1.0000
17.750 1.5128 0.08628 0.08094 -0.0370 0.0197 1.0000
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