CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK V AIRFOIL (clarkv-il) Reynolds number: 1,000,000 Max Cl/Cd: 129.42 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkv-il-1000000.txt Download as CSV file: xf-clarkv-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.9794 0.04433 0.04185 -0.0886 1.0000 0.0128
-14.500 -1.0410 0.03676 0.03405 -0.0904 1.0000 0.0126
-14.250 -1.0684 0.03430 0.03147 -0.0870 0.9993 0.0126
-14.000 -1.0560 0.03235 0.02937 -0.0882 0.9970 0.0129
-13.750 -1.0356 0.03058 0.02746 -0.0900 0.9953 0.0132
-13.500 -1.0134 0.02895 0.02567 -0.0917 0.9942 0.0136
-13.250 -0.9953 0.02769 0.02428 -0.0918 0.9917 0.0138
-13.000 -0.9720 0.02678 0.02324 -0.0924 0.9898 0.0141
-12.750 -0.9556 0.02458 0.02087 -0.0932 0.9875 0.0147
-12.500 -0.9270 0.02409 0.02035 -0.0943 0.9864 0.0151
-12.250 -0.8971 0.02373 0.01997 -0.0954 0.9856 0.0156
-12.000 -0.8676 0.02317 0.01935 -0.0967 0.9848 0.0160
-11.750 -0.8380 0.02248 0.01857 -0.0980 0.9841 0.0166
-11.500 -0.8078 0.02178 0.01775 -0.0994 0.9835 0.0171
-11.250 -0.7897 0.02129 0.01716 -0.0980 0.9794 0.0174
-11.000 -0.7676 0.01979 0.01549 -0.0982 0.9771 0.0180
-10.750 -0.7384 0.01925 0.01492 -0.0992 0.9758 0.0186
-10.500 -0.7068 0.01898 0.01464 -0.1005 0.9749 0.0191
-10.250 -0.6745 0.01872 0.01435 -0.1018 0.9742 0.0197
-10.000 -0.6421 0.01830 0.01385 -0.1033 0.9735 0.0205
-9.750 -0.6099 0.01785 0.01332 -0.1046 0.9729 0.0211
-9.500 -0.5774 0.01755 0.01293 -0.1059 0.9722 0.0215
-9.250 -0.5505 0.01600 0.01124 -0.1068 0.9711 0.0225
-9.000 -0.5317 0.01567 0.01090 -0.1052 0.9662 0.0231
-8.750 -0.5031 0.01538 0.01059 -0.1056 0.9640 0.0238
-8.500 -0.4738 0.01502 0.01018 -0.1062 0.9622 0.0245
-8.250 -0.4441 0.01456 0.00966 -0.1068 0.9606 0.0253
-8.000 -0.4140 0.01415 0.00918 -0.1074 0.9590 0.0259
-7.750 -0.3845 0.01394 0.00891 -0.1079 0.9571 0.0263
-7.500 -0.3665 0.01285 0.00773 -0.1062 0.9520 0.0274
-7.250 -0.3405 0.01230 0.00716 -0.1060 0.9489 0.0282
-7.000 -0.3126 0.01189 0.00672 -0.1062 0.9463 0.0289
-6.750 -0.2844 0.01155 0.00635 -0.1063 0.9439 0.0298
-6.500 -0.2594 0.01126 0.00602 -0.1058 0.9399 0.0306
-6.250 -0.2337 0.01091 0.00563 -0.1054 0.9358 0.0313
-6.000 -0.2063 0.01058 0.00526 -0.1053 0.9323 0.0318
-5.750 -0.1780 0.01032 0.00495 -0.1054 0.9293 0.0322
-5.500 -0.1545 0.00972 0.00429 -0.1046 0.9244 0.0335
-5.250 -0.1285 0.00935 0.00389 -0.1042 0.9198 0.0347
-5.000 -0.1009 0.00906 0.00358 -0.1042 0.9159 0.0358
-4.750 -0.0737 0.00883 0.00332 -0.1040 0.9115 0.0368
-4.500 -0.0471 0.00862 0.00308 -0.1037 0.9060 0.0380
-4.250 -0.0191 0.00843 0.00286 -0.1037 0.9014 0.0390
-4.000 0.0080 0.00818 0.00257 -0.1035 0.8963 0.0412
-3.750 0.0347 0.00797 0.00237 -0.1033 0.8903 0.0442
-3.500 0.0632 0.00781 0.00217 -0.1033 0.8852 0.0475
-3.250 0.0897 0.00761 0.00202 -0.1031 0.8787 0.0576
-3.000 0.1170 0.00739 0.00186 -0.1029 0.8725 0.0769
-2.750 0.1443 0.00722 0.00174 -0.1028 0.8663 0.0946
-2.500 0.1709 0.00700 0.00163 -0.1026 0.8592 0.1299
-2.250 0.1980 0.00681 0.00153 -0.1025 0.8526 0.1666
-2.000 0.2243 0.00657 0.00144 -0.1023 0.8449 0.2163
-1.750 0.2505 0.00633 0.00138 -0.1020 0.8366 0.2826
-1.500 0.2765 0.00615 0.00132 -0.1017 0.8262 0.3386
-1.250 0.3025 0.00599 0.00128 -0.1013 0.8148 0.3906
-1.000 0.3283 0.00582 0.00126 -0.1009 0.8046 0.4512
-0.750 0.3540 0.00565 0.00124 -0.1005 0.7953 0.5174
-0.500 0.3792 0.00543 0.00124 -0.1000 0.7858 0.5972
-0.250 0.4030 0.00518 0.00126 -0.0991 0.7764 0.6994
0.000 0.4261 0.00497 0.00130 -0.0980 0.7662 0.7910
0.250 0.4501 0.00486 0.00136 -0.0970 0.7559 0.8532
0.500 0.4745 0.00484 0.00141 -0.0959 0.7443 0.9001
0.750 0.5001 0.00490 0.00148 -0.0952 0.7299 0.9391
1.000 0.5309 0.00501 0.00154 -0.0956 0.7124 0.9635
1.250 0.5653 0.00515 0.00160 -0.0970 0.6959 0.9794
1.500 0.6025 0.00527 0.00166 -0.0991 0.6813 0.9861
1.750 0.6417 0.00541 0.00172 -0.1016 0.6647 0.9920
2.000 0.6790 0.00555 0.00178 -0.1038 0.6480 0.9956
2.250 0.7158 0.00567 0.00184 -0.1059 0.6317 0.9986
2.500 0.7454 0.00581 0.00190 -0.1064 0.6154 1.0000
2.750 0.7670 0.00594 0.00197 -0.1051 0.5989 1.0000
3.000 0.7879 0.00609 0.00204 -0.1037 0.5807 1.0000
3.250 0.8089 0.00625 0.00213 -0.1023 0.5605 1.0000
3.500 0.8288 0.00645 0.00223 -0.1007 0.5366 1.0000
3.750 0.8488 0.00667 0.00234 -0.0990 0.5115 1.0000
4.000 0.8684 0.00691 0.00247 -0.0974 0.4860 1.0000
4.250 0.8876 0.00718 0.00262 -0.0956 0.4563 1.0000
4.500 0.9072 0.00748 0.00278 -0.0940 0.4259 1.0000
4.750 0.9272 0.00780 0.00297 -0.0925 0.3959 1.0000
5.000 0.9473 0.00814 0.00317 -0.0910 0.3655 1.0000
5.250 0.9686 0.00845 0.00338 -0.0898 0.3403 1.0000
5.500 0.9900 0.00877 0.00360 -0.0886 0.3175 1.0000
5.750 1.0110 0.00913 0.00383 -0.0874 0.2913 1.0000
6.000 1.0322 0.00948 0.00407 -0.0863 0.2661 1.0000
6.250 1.0532 0.00985 0.00433 -0.0851 0.2425 1.0000
6.500 1.0739 0.01025 0.00460 -0.0839 0.2171 1.0000
6.750 1.0945 0.01065 0.00489 -0.0827 0.1950 1.0000
7.000 1.1150 0.01104 0.00519 -0.0814 0.1758 1.0000
7.250 1.1363 0.01139 0.00549 -0.0803 0.1619 1.0000
7.500 1.1570 0.01173 0.00578 -0.0792 0.1489 1.0000
7.750 1.1765 0.01211 0.00610 -0.0777 0.1344 1.0000
8.000 1.1944 0.01258 0.00646 -0.0761 0.1161 1.0000
8.250 1.2118 0.01309 0.00688 -0.0743 0.0972 1.0000
8.500 1.2291 0.01362 0.00732 -0.0726 0.0825 1.0000
8.750 1.2461 0.01415 0.00779 -0.0709 0.0694 1.0000
9.000 1.2613 0.01481 0.00835 -0.0689 0.0521 1.0000
9.250 1.2720 0.01575 0.00912 -0.0662 0.0306 1.0000
9.500 1.2867 0.01646 0.00979 -0.0642 0.0228 1.0000
9.750 1.3022 0.01712 0.01044 -0.0624 0.0195 1.0000
10.000 1.3189 0.01769 0.01104 -0.0607 0.0180 1.0000
10.250 1.3332 0.01841 0.01179 -0.0588 0.0164 1.0000
10.500 1.3487 0.01906 0.01249 -0.0571 0.0156 1.0000
10.750 1.3646 0.01969 0.01317 -0.0555 0.0149 1.0000
11.000 1.3794 0.02038 0.01391 -0.0538 0.0143 1.0000
11.250 1.3927 0.02119 0.01475 -0.0519 0.0136 1.0000
11.500 1.4010 0.02234 0.01597 -0.0494 0.0128 1.0000
11.750 1.4142 0.02315 0.01685 -0.0477 0.0124 1.0000
12.000 1.4275 0.02398 0.01773 -0.0461 0.0121 1.0000
12.250 1.4394 0.02491 0.01873 -0.0443 0.0117 1.0000
12.500 1.4503 0.02593 0.01980 -0.0425 0.0113 1.0000
12.750 1.4604 0.02703 0.02096 -0.0408 0.0110 1.0000
13.000 1.4691 0.02825 0.02225 -0.0390 0.0107 1.0000
13.250 1.4746 0.02975 0.02382 -0.0370 0.0104 1.0000
13.500 1.4738 0.03180 0.02597 -0.0346 0.0100 1.0000
13.750 1.4726 0.03398 0.02826 -0.0324 0.0098 1.0000
14.000 1.4801 0.03548 0.02984 -0.0311 0.0097 1.0000
14.250 1.4862 0.03715 0.03159 -0.0298 0.0095 1.0000
14.500 1.4905 0.03905 0.03358 -0.0285 0.0094 1.0000
14.750 1.4938 0.04111 0.03573 -0.0274 0.0092 1.0000
15.000 1.4968 0.04328 0.03799 -0.0264 0.0090 1.0000
15.250 1.4986 0.04566 0.04046 -0.0256 0.0088 1.0000
15.500 1.5002 0.04815 0.04304 -0.0250 0.0086 1.0000
15.750 1.5006 0.05087 0.04584 -0.0246 0.0085 1.0000
16.000 1.5001 0.05376 0.04882 -0.0243 0.0083 1.0000
16.250 1.4980 0.05697 0.05211 -0.0242 0.0082 1.0000
16.500 1.4937 0.06056 0.05581 -0.0243 0.0081 1.0000
16.750 1.4869 0.06460 0.05994 -0.0247 0.0080 1.0000
17.000 1.4776 0.06907 0.06452 -0.0254 0.0079 1.0000
17.250 1.4655 0.07408 0.06965 -0.0263 0.0078 1.0000
17.500 1.4513 0.07954 0.07523 -0.0276 0.0077 1.0000
17.750 1.4350 0.08540 0.08121 -0.0291 0.0076 1.0000
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Polar data table (+)
Polar graphs
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