CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: CLARK V AIRFOIL (clarkv-il) Reynolds number: 500,000 Max Cl/Cd: 110.42 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkv-il-500000.txt Download as CSV file: xf-clarkv-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4826 0.09144 0.08924 -0.0432 0.9994 0.0326
-9.750 -0.5294 0.07145 0.06928 -0.0574 0.9955 0.0271
-9.500 -0.6205 0.03791 0.03464 -0.0854 0.9793 0.0249
-9.250 -0.6151 0.03177 0.02775 -0.0868 0.9745 0.0258
-9.000 -0.5959 0.02781 0.02320 -0.0884 0.9723 0.0269
-8.750 -0.5657 0.02653 0.02187 -0.0902 0.9713 0.0279
-8.500 -0.5472 0.02611 0.02145 -0.0889 0.9656 0.0287
-8.250 -0.5195 0.02496 0.02015 -0.0897 0.9630 0.0297
-8.000 -0.4906 0.02339 0.01830 -0.0908 0.9611 0.0308
-7.750 -0.4585 0.02231 0.01696 -0.0922 0.9597 0.0319
-7.500 -0.4283 0.02023 0.01458 -0.0936 0.9586 0.0332
-7.250 -0.3944 0.01917 0.01347 -0.0955 0.9579 0.0343
-7.000 -0.3765 0.01855 0.01279 -0.0937 0.9515 0.0351
-6.750 -0.3451 0.01784 0.01199 -0.0947 0.9492 0.0363
-6.500 -0.3112 0.01715 0.01121 -0.0961 0.9477 0.0377
-6.250 -0.2761 0.01643 0.01038 -0.0978 0.9466 0.0386
-6.000 -0.2410 0.01585 0.00970 -0.0994 0.9455 0.0393
-5.750 -0.2090 0.01447 0.00825 -0.1006 0.9443 0.0410
-5.500 -0.1749 0.01387 0.00764 -0.1021 0.9432 0.0425
-5.250 -0.1569 0.01350 0.00724 -0.1000 0.9359 0.0435
-5.000 -0.1257 0.01299 0.00671 -0.1007 0.9334 0.0450
-4.750 -0.0934 0.01252 0.00619 -0.1017 0.9314 0.0465
-4.500 -0.0605 0.01213 0.00576 -0.1027 0.9296 0.0479
-4.250 -0.0372 0.01157 0.00519 -0.1018 0.9244 0.0508
-4.000 -0.0096 0.01122 0.00484 -0.1017 0.9200 0.0536
-3.750 0.0212 0.01089 0.00448 -0.1022 0.9171 0.0571
-3.500 0.0526 0.01043 0.00404 -0.1029 0.9146 0.0648
-3.250 0.0762 0.01012 0.00379 -0.1020 0.9083 0.0788
-3.000 0.1041 0.00971 0.00348 -0.1020 0.9038 0.1077
-2.750 0.1342 0.00928 0.00322 -0.1025 0.9004 0.1558
-2.500 0.1587 0.00891 0.00307 -0.1019 0.8943 0.2132
-2.250 0.1855 0.00849 0.00291 -0.1018 0.8889 0.2952
-2.000 0.2148 0.00811 0.00275 -0.1022 0.8848 0.3690
-1.750 0.2388 0.00786 0.00269 -0.1014 0.8773 0.4316
-1.500 0.2662 0.00752 0.00257 -0.1013 0.8718 0.5072
-1.250 0.2905 0.00717 0.00252 -0.1006 0.8648 0.5988
-1.000 0.3142 0.00677 0.00248 -0.0995 0.8576 0.7081
-0.750 0.3366 0.00647 0.00248 -0.0979 0.8485 0.8068
-0.500 0.3626 0.00631 0.00246 -0.0968 0.8393 0.8851
-0.250 0.3914 0.00630 0.00248 -0.0965 0.8288 0.9268
0.000 0.4255 0.00634 0.00248 -0.0976 0.8205 0.9523
0.250 0.4662 0.00640 0.00248 -0.1001 0.8121 0.9727
0.500 0.5132 0.00647 0.00250 -0.1042 0.8034 0.9853
1.000 0.6054 0.00653 0.00244 -0.1121 0.7830 1.0000
1.250 0.6288 0.00657 0.00240 -0.1112 0.7688 1.0000
1.500 0.6516 0.00662 0.00238 -0.1101 0.7529 1.0000
1.750 0.6744 0.00669 0.00238 -0.1091 0.7378 1.0000
2.000 0.6974 0.00677 0.00240 -0.1081 0.7243 1.0000
2.250 0.7202 0.00686 0.00243 -0.1070 0.7102 1.0000
2.500 0.7425 0.00696 0.00248 -0.1058 0.6949 1.0000
2.750 0.7645 0.00708 0.00254 -0.1045 0.6791 1.0000
3.000 0.7865 0.00721 0.00261 -0.1033 0.6635 1.0000
3.250 0.8082 0.00736 0.00269 -0.1020 0.6475 1.0000
3.500 0.8295 0.00752 0.00279 -0.1006 0.6306 1.0000
3.750 0.8502 0.00770 0.00290 -0.0991 0.6122 1.0000
4.000 0.8706 0.00789 0.00302 -0.0975 0.5913 1.0000
4.250 0.8905 0.00812 0.00316 -0.0958 0.5683 1.0000
4.500 0.9101 0.00836 0.00331 -0.0941 0.5429 1.0000
4.750 0.9290 0.00866 0.00349 -0.0923 0.5143 1.0000
5.000 0.9481 0.00897 0.00368 -0.0906 0.4857 1.0000
5.250 0.9674 0.00930 0.00390 -0.0889 0.4570 1.0000
5.500 0.9862 0.00968 0.00415 -0.0872 0.4253 1.0000
5.750 1.0047 0.01010 0.00443 -0.0855 0.3926 1.0000
6.000 1.0234 0.01053 0.00473 -0.0838 0.3638 1.0000
6.250 1.0422 0.01097 0.00505 -0.0822 0.3363 1.0000
6.500 1.0609 0.01143 0.00539 -0.0806 0.3085 1.0000
6.750 1.0796 0.01189 0.00573 -0.0791 0.2818 1.0000
7.000 1.0978 0.01237 0.00609 -0.0774 0.2562 1.0000
7.250 1.1151 0.01285 0.00645 -0.0756 0.2305 1.0000
7.500 1.1328 0.01332 0.00684 -0.0739 0.2087 1.0000
7.750 1.1507 0.01379 0.00723 -0.0723 0.1907 1.0000
8.000 1.1685 0.01429 0.00766 -0.0707 0.1741 1.0000
8.250 1.1861 0.01479 0.00811 -0.0690 0.1586 1.0000
8.500 1.2038 0.01531 0.00857 -0.0675 0.1435 1.0000
8.750 1.2209 0.01586 0.00906 -0.0658 0.1271 1.0000
9.000 1.2372 0.01647 0.00959 -0.0641 0.1078 1.0000
9.250 1.2509 0.01724 0.01025 -0.0621 0.0885 1.0000
9.500 1.2640 0.01806 0.01098 -0.0599 0.0694 1.0000
9.750 1.2723 0.01922 0.01195 -0.0572 0.0440 1.0000
10.000 1.2809 0.02038 0.01301 -0.0545 0.0316 1.0000
10.250 1.2932 0.02130 0.01396 -0.0524 0.0275 1.0000
10.500 1.3026 0.02241 0.01509 -0.0499 0.0247 1.0000
10.750 1.3161 0.02325 0.01601 -0.0481 0.0231 1.0000
11.000 1.3274 0.02424 0.01706 -0.0462 0.0217 1.0000
11.250 1.3343 0.02556 0.01843 -0.0437 0.0205 1.0000
11.500 1.3409 0.02692 0.01988 -0.0414 0.0197 1.0000
11.750 1.3505 0.02809 0.02114 -0.0395 0.0190 1.0000
12.000 1.3586 0.02940 0.02254 -0.0376 0.0184 1.0000
12.250 1.3655 0.03083 0.02406 -0.0356 0.0178 1.0000
12.500 1.3710 0.03241 0.02571 -0.0338 0.0172 1.0000
12.750 1.3731 0.03433 0.02769 -0.0318 0.0167 1.0000
13.000 1.3684 0.03688 0.03034 -0.0294 0.0161 1.0000
13.250 1.3711 0.03891 0.03247 -0.0279 0.0158 1.0000
13.500 1.3766 0.04075 0.03441 -0.0266 0.0154 1.0000
13.750 1.3799 0.04282 0.03659 -0.0254 0.0151 1.0000
14.000 1.3820 0.04509 0.03896 -0.0243 0.0148 1.0000
14.250 1.3836 0.04750 0.04148 -0.0234 0.0144 1.0000
14.500 1.3844 0.05005 0.04414 -0.0226 0.0142 1.0000
14.750 1.3846 0.05275 0.04693 -0.0219 0.0139 1.0000
15.000 1.3840 0.05562 0.04988 -0.0214 0.0136 1.0000
15.250 1.3827 0.05865 0.05300 -0.0211 0.0134 1.0000
15.500 1.3802 0.06186 0.05629 -0.0208 0.0132 1.0000
15.750 1.3760 0.06527 0.05978 -0.0205 0.0130 1.0000
16.000 1.3704 0.06884 0.06345 -0.0199 0.0128 1.0000
16.250 1.3657 0.07248 0.06722 -0.0197 0.0126 1.0000
16.500 1.3626 0.07619 0.07106 -0.0203 0.0125 1.0000
16.750 1.3584 0.08013 0.07517 -0.0211 0.0124 1.0000
17.000 1.3533 0.08432 0.07950 -0.0221 0.0123 1.0000
17.250 1.3473 0.08875 0.08408 -0.0233 0.0122 1.0000
17.500 1.3405 0.09340 0.08887 -0.0248 0.0120 1.0000
17.750 1.3327 0.09828 0.09391 -0.0265 0.0119 1.0000
18.000 1.3242 0.10341 0.09918 -0.0285 0.0118 1.0000
18.250 1.3153 0.10873 0.10464 -0.0308 0.0116 1.0000
18.500 1.3056 0.11433 0.11039 -0.0333 0.0115 1.0000
18.750 1.2956 0.12010 0.11630 -0.0361 0.0114 1.0000
19.000 1.2845 0.12618 0.12252 -0.0393 0.0114 1.0000
19.250 1.2736 0.13243 0.12891 -0.0427 0.0113 1.0000
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