CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK V AIRFOIL (clarkv-il) Reynolds number: 200,000 Max Cl/Cd: 80.92 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkv-il-200000.txt Download as CSV file: xf-clarkv-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: CLARK V 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4209 0.10285 0.09931 -0.0364 1.0000 0.0658
-9.250 -0.4407 0.09970 0.09625 -0.0374 1.0000 0.0680
-9.000 -0.4730 0.09659 0.09325 -0.0389 1.0000 0.0690
-8.750 -0.4065 0.08861 0.08557 -0.0327 1.0000 0.0713
-8.500 -0.4046 0.08678 0.08375 -0.0302 1.0000 0.0723
-8.250 -0.4041 0.08417 0.08117 -0.0294 0.9994 0.0739
-8.000 -0.3989 0.07960 0.07659 -0.0326 0.9965 0.0769
-7.750 -0.5563 0.07808 0.07494 -0.0369 0.9995 0.0712
-7.500 -0.5350 0.07618 0.07303 -0.0368 0.9969 0.0729
-7.250 -0.5147 0.07172 0.06850 -0.0418 0.9927 0.0757
-7.000 -0.5092 0.05864 0.05471 -0.0577 0.9839 0.0838
-6.750 -0.4095 0.04697 0.04365 -0.0607 0.9710 0.0894
-6.500 -0.4825 0.03860 0.03294 -0.0624 0.9737 0.0582
-6.250 -0.4507 0.03545 0.02933 -0.0646 0.9714 0.0580
-6.000 -0.4302 0.03201 0.02549 -0.0645 0.9661 0.0583
-5.750 -0.4007 0.02933 0.02243 -0.0656 0.9626 0.0584
-5.500 -0.3675 0.02690 0.01972 -0.0675 0.9602 0.0596
-5.250 -0.3305 0.02573 0.01844 -0.0698 0.9581 0.0620
-5.000 -0.3047 0.02460 0.01713 -0.0696 0.9526 0.0632
-4.750 -0.2719 0.02348 0.01581 -0.0707 0.9487 0.0646
-4.500 -0.2350 0.02260 0.01474 -0.0725 0.9459 0.0670
-4.250 -0.1953 0.02204 0.01399 -0.0748 0.9438 0.0694
-4.000 -0.1705 0.02080 0.01274 -0.0745 0.9381 0.0718
-3.750 -0.1374 0.02008 0.01205 -0.0757 0.9339 0.0753
-3.500 -0.1000 0.01950 0.01144 -0.0776 0.9310 0.0804
-3.250 -0.0607 0.01873 0.01071 -0.0800 0.9291 0.0884
-3.000 -0.0384 0.01835 0.01032 -0.0790 0.9213 0.0973
-2.750 -0.0029 0.01762 0.00977 -0.0807 0.9177 0.1233
-2.500 0.0356 0.01670 0.00929 -0.0832 0.9155 0.2072
-2.250 0.0620 0.01601 0.00923 -0.0835 0.9096 0.3573
-2.000 0.0925 0.01548 0.00911 -0.0842 0.9045 0.4723
-1.750 0.1268 0.01477 0.00898 -0.0853 0.9017 0.6139
-1.500 0.1578 0.01406 0.00896 -0.0848 0.8998 0.7992
-1.250 0.2064 0.01387 0.00894 -0.0877 0.8992 0.9338
-1.000 0.2782 0.01379 0.00876 -0.0966 0.8996 0.9884
-0.750 0.3144 0.01381 0.00868 -0.0986 0.8919 1.0000
-0.500 0.3523 0.01354 0.00832 -0.1006 0.8880 1.0000
-0.250 0.3939 0.01322 0.00791 -0.1032 0.8855 1.0000
0.000 0.4136 0.01315 0.00778 -0.1014 0.8756 1.0000
0.250 0.4561 0.01266 0.00722 -0.1039 0.8716 1.0000
0.500 0.4819 0.01242 0.00692 -0.1031 0.8619 1.0000
0.750 0.5203 0.01201 0.00646 -0.1048 0.8567 1.0000
1.000 0.5442 0.01192 0.00632 -0.1038 0.8473 1.0000
1.250 0.5798 0.01162 0.00599 -0.1050 0.8414 1.0000
1.500 0.6035 0.01157 0.00590 -0.1039 0.8311 1.0000
1.750 0.6395 0.01130 0.00559 -0.1052 0.8246 1.0000
2.000 0.6623 0.01128 0.00555 -0.1039 0.8129 1.0000
2.250 0.6880 0.01121 0.00546 -0.1032 0.8013 1.0000
2.500 0.7153 0.01109 0.00530 -0.1027 0.7884 1.0000
2.750 0.7418 0.01101 0.00518 -0.1020 0.7743 1.0000
3.000 0.7679 0.01099 0.00511 -0.1013 0.7605 1.0000
3.250 0.7939 0.01100 0.00509 -0.1007 0.7470 1.0000
3.500 0.8190 0.01105 0.00510 -0.0999 0.7327 1.0000
3.750 0.8428 0.01112 0.00516 -0.0989 0.7170 1.0000
4.000 0.8659 0.01122 0.00523 -0.0977 0.7000 1.0000
4.250 0.8889 0.01134 0.00533 -0.0965 0.6824 1.0000
4.500 0.9120 0.01148 0.00544 -0.0953 0.6640 1.0000
4.750 0.9348 0.01164 0.00555 -0.0941 0.6440 1.0000
5.000 0.9560 0.01184 0.00569 -0.0926 0.6215 1.0000
5.250 0.9767 0.01207 0.00585 -0.0910 0.5965 1.0000
5.500 0.9953 0.01235 0.00604 -0.0890 0.5674 1.0000
5.750 1.0132 0.01268 0.00626 -0.0869 0.5366 1.0000
6.000 1.0307 0.01305 0.00653 -0.0848 0.5055 1.0000
6.250 1.0472 0.01348 0.00685 -0.0826 0.4736 1.0000
6.500 1.0628 0.01397 0.00720 -0.0802 0.4408 1.0000
6.750 1.0776 0.01451 0.00761 -0.0778 0.4081 1.0000
7.000 1.0920 0.01510 0.00806 -0.0754 0.3780 1.0000
7.250 1.1063 0.01573 0.00858 -0.0730 0.3509 1.0000
7.500 1.1209 0.01635 0.00911 -0.0707 0.3250 1.0000
7.750 1.1336 0.01700 0.00965 -0.0681 0.3004 1.0000
8.000 1.1456 0.01765 0.01020 -0.0655 0.2756 1.0000
8.250 1.1585 0.01828 0.01076 -0.0631 0.2507 1.0000
8.500 1.1709 0.01899 0.01138 -0.0607 0.2294 1.0000
8.750 1.1851 0.01966 0.01202 -0.0586 0.2105 1.0000
9.000 1.1988 0.02037 0.01271 -0.0566 0.1923 1.0000
9.250 1.2118 0.02115 0.01345 -0.0545 0.1748 1.0000
9.500 1.2239 0.02199 0.01425 -0.0524 0.1579 1.0000
9.750 1.2364 0.02284 0.01510 -0.0504 0.1393 1.0000
10.000 1.2475 0.02381 0.01600 -0.0482 0.1165 1.0000
10.250 1.2531 0.02521 0.01722 -0.0456 0.0896 1.0000
10.500 1.2532 0.02710 0.01894 -0.0423 0.0664 1.0000
10.750 1.2542 0.02895 0.02073 -0.0392 0.0545 1.0000
11.000 1.2599 0.03049 0.02232 -0.0368 0.0480 1.0000
11.250 1.2621 0.03233 0.02421 -0.0342 0.0441 1.0000
11.500 1.2682 0.03392 0.02587 -0.0322 0.0408 1.0000
11.750 1.2700 0.03589 0.02787 -0.0300 0.0387 1.0000
12.000 1.2710 0.03807 0.03009 -0.0277 0.0371 1.0000
12.250 1.2775 0.03983 0.03200 -0.0260 0.0357 1.0000
12.500 1.2834 0.04169 0.03395 -0.0244 0.0342 1.0000
12.750 1.2888 0.04361 0.03593 -0.0229 0.0328 1.0000
13.000 1.2932 0.04569 0.03804 -0.0214 0.0316 1.0000
13.250 1.2998 0.04793 0.04032 -0.0197 0.0304 1.0000
13.500 1.3067 0.04993 0.04249 -0.0185 0.0296 1.0000
13.750 1.3134 0.05205 0.04477 -0.0172 0.0289 1.0000
14.000 1.3196 0.05428 0.04716 -0.0160 0.0282 1.0000
14.250 1.3247 0.05668 0.04970 -0.0148 0.0276 1.0000
14.500 1.3283 0.05924 0.05242 -0.0138 0.0271 1.0000
14.750 1.3300 0.06195 0.05528 -0.0129 0.0266 1.0000
15.000 1.3308 0.06478 0.05825 -0.0122 0.0261 1.0000
15.250 1.3326 0.06770 0.06126 -0.0115 0.0256 1.0000
15.500 1.3334 0.07129 0.06498 -0.0107 0.0250 1.0000
15.750 1.3228 0.07579 0.06970 -0.0104 0.0248 1.0000
16.000 1.3090 0.08026 0.07443 -0.0109 0.0247 1.0000
16.250 1.2942 0.08520 0.07961 -0.0119 0.0246 1.0000
16.500 1.2784 0.09058 0.08523 -0.0134 0.0245 1.0000
16.750 1.2616 0.09645 0.09133 -0.0154 0.0245 1.0000
17.000 1.2437 0.10282 0.09792 -0.0181 0.0245 1.0000
17.250 1.2252 0.10967 0.10498 -0.0214 0.0246 1.0000
17.500 1.2059 0.11701 0.11252 -0.0252 0.0246 1.0000
17.750 1.1861 0.12487 0.12057 -0.0297 0.0247 1.0000
18.000 1.1665 0.13318 0.12906 -0.0348 0.0249 1.0000
18.250 1.1427 0.14352 0.13965 -0.0426 0.0252 1.0000
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