CLARK K AIRFOIL (clarkk-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK K AIRFOIL (clarkk-il) Reynolds number: 200,000 Max Cl/Cd: 71.52 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkk-il-200000-n5.txt Download as CSV file: xf-clarkk-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CLARK K 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4269 0.08925 0.08536 -0.0448 1.0000 0.0420
-9.750 -0.4372 0.08400 0.08015 -0.0473 1.0000 0.0428
-9.500 -0.4575 0.07776 0.07399 -0.0501 1.0000 0.0434
-9.250 -0.4970 0.07083 0.06718 -0.0522 1.0000 0.0437
-9.000 -0.5716 0.04720 0.04254 -0.0735 0.9851 0.0454
-8.750 -0.5448 0.04600 0.04142 -0.0747 0.9814 0.0460
-8.500 -0.5215 0.04383 0.03913 -0.0768 0.9766 0.0468
-8.250 -0.4984 0.04108 0.03615 -0.0792 0.9723 0.0478
-8.000 -0.4777 0.03831 0.03307 -0.0808 0.9661 0.0492
-7.750 -0.4533 0.03529 0.02956 -0.0830 0.9621 0.0505
-7.500 -0.4331 0.03304 0.02688 -0.0833 0.9547 0.0514
-7.250 -0.4051 0.03185 0.02510 -0.0844 0.9505 0.0526
-7.000 -0.3836 0.02935 0.02247 -0.0846 0.9434 0.0533
-6.750 -0.3551 0.02773 0.02071 -0.0855 0.9391 0.0539
-6.500 -0.3284 0.02640 0.01925 -0.0859 0.9333 0.0544
-6.250 -0.3015 0.02521 0.01792 -0.0862 0.9271 0.0549
-6.000 -0.2712 0.02414 0.01669 -0.0871 0.9229 0.0558
-5.750 -0.2469 0.02325 0.01566 -0.0867 0.9146 0.0567
-5.500 -0.2177 0.02227 0.01451 -0.0871 0.9092 0.0572
-5.250 -0.1915 0.02142 0.01349 -0.0869 0.9016 0.0576
-5.000 -0.1636 0.02061 0.01253 -0.0869 0.8949 0.0580
-4.750 -0.1356 0.01987 0.01166 -0.0869 0.8883 0.0584
-4.500 -0.1089 0.01922 0.01088 -0.0867 0.8804 0.0588
-4.000 -0.0538 0.01816 0.00960 -0.0864 0.8658 0.0601
-3.750 -0.0252 0.01770 0.00903 -0.0864 0.8592 0.0607
-3.500 0.0014 0.01725 0.00852 -0.0861 0.8508 0.0610
-3.250 0.0293 0.01679 0.00798 -0.0859 0.8435 0.0612
-3.000 0.0563 0.01635 0.00752 -0.0857 0.8353 0.0615
-2.750 0.0833 0.01570 0.00688 -0.0854 0.8276 0.0619
-2.500 0.1098 0.01518 0.00637 -0.0852 0.8196 0.0624
-2.250 0.1365 0.01473 0.00594 -0.0849 0.8112 0.0629
-2.000 0.1630 0.01435 0.00558 -0.0845 0.8030 0.0635
-1.750 0.1897 0.01403 0.00526 -0.0842 0.7945 0.0641
-1.500 0.2162 0.01375 0.00500 -0.0839 0.7858 0.0649
-1.250 0.2430 0.01350 0.00474 -0.0836 0.7772 0.0662
-1.000 0.2696 0.01330 0.00454 -0.0833 0.7679 0.0676
-0.750 0.2968 0.01313 0.00432 -0.0830 0.7592 0.0686
-0.500 0.3233 0.01299 0.00416 -0.0827 0.7492 0.0693
-0.250 0.3505 0.01287 0.00399 -0.0824 0.7401 0.0700
0.000 0.3773 0.01277 0.00387 -0.0821 0.7296 0.0708
0.250 0.4041 0.01270 0.00375 -0.0818 0.7191 0.0716
0.500 0.4311 0.01261 0.00361 -0.0814 0.7087 0.0731
0.750 0.4575 0.01254 0.00351 -0.0810 0.6963 0.0749
1.000 0.4838 0.01249 0.00343 -0.0805 0.6822 0.0772
1.250 0.5100 0.01246 0.00336 -0.0801 0.6671 0.0804
1.500 0.5361 0.01242 0.00332 -0.0796 0.6525 0.0892
1.750 0.5612 0.01211 0.00336 -0.0792 0.6395 0.2132
2.000 0.5862 0.01187 0.00342 -0.0787 0.6266 0.3104
2.250 0.6002 0.01054 0.00366 -0.0757 0.6142 0.7949
2.500 0.6589 0.01043 0.00376 -0.0817 0.5972 0.9993
2.750 0.6835 0.01058 0.00382 -0.0810 0.5829 1.0000
3.000 0.7077 0.01074 0.00391 -0.0802 0.5686 1.0000
3.250 0.7318 0.01092 0.00400 -0.0794 0.5535 1.0000
3.500 0.7557 0.01111 0.00411 -0.0785 0.5380 1.0000
3.750 0.7797 0.01132 0.00425 -0.0777 0.5228 1.0000
4.000 0.8035 0.01153 0.00440 -0.0769 0.5073 1.0000
4.250 0.8271 0.01177 0.00457 -0.0760 0.4904 1.0000
4.500 0.8506 0.01202 0.00476 -0.0752 0.4731 1.0000
4.750 0.8740 0.01228 0.00497 -0.0743 0.4560 1.0000
5.000 0.8971 0.01256 0.00519 -0.0734 0.4383 1.0000
5.250 0.9198 0.01286 0.00544 -0.0725 0.4193 1.0000
5.500 0.9421 0.01319 0.00570 -0.0715 0.4000 1.0000
5.750 0.9642 0.01355 0.00600 -0.0705 0.3815 1.0000
6.000 0.9861 0.01392 0.00632 -0.0694 0.3640 1.0000
6.250 1.0077 0.01431 0.00666 -0.0684 0.3461 1.0000
6.500 1.0287 0.01474 0.00703 -0.0673 0.3262 1.0000
6.750 1.0490 0.01520 0.00743 -0.0661 0.3067 1.0000
7.000 1.0690 0.01569 0.00784 -0.0648 0.2880 1.0000
7.250 1.0884 0.01621 0.00829 -0.0635 0.2698 1.0000
7.500 1.1072 0.01675 0.00876 -0.0622 0.2514 1.0000
7.750 1.1260 0.01729 0.00924 -0.0608 0.2346 1.0000
8.000 1.1450 0.01782 0.00974 -0.0595 0.2194 1.0000
8.250 1.1629 0.01840 0.01028 -0.0581 0.2026 1.0000
8.500 1.1806 0.01897 0.01083 -0.0567 0.1850 1.0000
8.750 1.1970 0.01958 0.01140 -0.0550 0.1648 1.0000
9.000 1.2102 0.02034 0.01205 -0.0529 0.1404 1.0000
9.250 1.2184 0.02146 0.01295 -0.0503 0.1028 1.0000
9.750 1.2274 0.02441 0.01549 -0.0446 0.0457 1.0000
10.000 1.2360 0.02564 0.01670 -0.0424 0.0384 1.0000
10.250 1.2463 0.02676 0.01789 -0.0405 0.0347 1.0000
10.500 1.2552 0.02801 0.01921 -0.0386 0.0319 1.0000
10.750 1.2610 0.02952 0.02078 -0.0365 0.0297 1.0000
11.000 1.2699 0.03082 0.02220 -0.0349 0.0283 1.0000
11.250 1.2772 0.03230 0.02380 -0.0332 0.0271 1.0000
11.500 1.2829 0.03394 0.02555 -0.0317 0.0260 1.0000
11.750 1.2871 0.03578 0.02749 -0.0302 0.0249 1.0000
12.000 1.2883 0.03794 0.02975 -0.0288 0.0241 1.0000
12.250 1.2855 0.04058 0.03248 -0.0275 0.0233 1.0000
12.500 1.2893 0.04269 0.03471 -0.0266 0.0226 1.0000
12.750 1.2916 0.04501 0.03716 -0.0258 0.0219 1.0000
13.000 1.2926 0.04755 0.03982 -0.0251 0.0214 1.0000
13.250 1.2924 0.05027 0.04265 -0.0245 0.0209 1.0000
13.500 1.2918 0.05311 0.04560 -0.0241 0.0204 1.0000
13.750 1.2907 0.05609 0.04868 -0.0239 0.0199 1.0000
14.000 1.2891 0.05921 0.05189 -0.0239 0.0195 1.0000
14.250 1.2869 0.06249 0.05526 -0.0239 0.0191 1.0000
14.500 1.2837 0.06596 0.05880 -0.0241 0.0187 1.0000
14.750 1.2799 0.06948 0.06238 -0.0242 0.0184 1.0000
15.000 1.2799 0.07274 0.06579 -0.0246 0.0180 1.0000
15.250 1.2791 0.07615 0.06933 -0.0251 0.0176 1.0000
15.500 1.2779 0.07966 0.07298 -0.0257 0.0172 1.0000
15.750 1.2763 0.08327 0.07670 -0.0263 0.0169 1.0000
16.000 1.2745 0.08692 0.08048 -0.0270 0.0166 1.0000
16.250 1.2725 0.09067 0.08434 -0.0279 0.0163 1.0000
16.500 1.2704 0.09449 0.08828 -0.0288 0.0161 1.0000
16.750 1.2681 0.09838 0.09228 -0.0299 0.0158 1.0000
17.000 1.2656 0.10234 0.09634 -0.0311 0.0156 1.0000
17.250 1.2630 0.10636 0.10045 -0.0324 0.0154 1.0000
17.500 1.2607 0.11038 0.10457 -0.0339 0.0152 1.0000
17.750 1.2584 0.11440 0.10866 -0.0354 0.0150 1.0000
18.000 1.2567 0.11829 0.11261 -0.0368 0.0147 1.0000
18.250 1.2524 0.12282 0.11726 -0.0387 0.0146 1.0000
18.500 1.2449 0.12828 0.12290 -0.0415 0.0144 1.0000
18.750 1.2366 0.13406 0.12888 -0.0446 0.0142 1.0000
19.000 1.2275 0.14016 0.13516 -0.0481 0.0141 1.0000
19.250 1.2175 0.14664 0.14183 -0.0519 0.0139 1.0000
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