CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: CLARK V AIRFOIL (clarkv-il) Reynolds number: 200,000 Max Cl/Cd: 75.19 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-clarkv-il-200000-n5.txt Download as CSV file: xf-clarkv-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4791 0.09036 0.08683 -0.0434 1.0000 0.0257
-9.750 -0.4967 0.08382 0.08034 -0.0463 0.9988 0.0260
-9.500 -0.5881 0.04987 0.04601 -0.0785 0.9835 0.0257
-9.250 -0.6056 0.03933 0.03456 -0.0833 0.9753 0.0270
-9.000 -0.6014 0.03455 0.02899 -0.0834 0.9690 0.0283
-8.750 -0.5789 0.03286 0.02719 -0.0842 0.9658 0.0293
-8.500 -0.5522 0.03157 0.02575 -0.0854 0.9636 0.0303
-8.250 -0.5294 0.03011 0.02405 -0.0857 0.9602 0.0314
-8.000 -0.5091 0.02871 0.02240 -0.0853 0.9553 0.0328
-7.750 -0.4833 0.02703 0.02033 -0.0859 0.9524 0.0343
-7.500 -0.4541 0.02556 0.01847 -0.0869 0.9503 0.0353
-7.250 -0.4241 0.02401 0.01676 -0.0883 0.9488 0.0367
-7.000 -0.4063 0.02332 0.01600 -0.0867 0.9423 0.0378
-6.750 -0.3778 0.02245 0.01500 -0.0872 0.9392 0.0390
-6.500 -0.3467 0.02150 0.01389 -0.0882 0.9370 0.0401
-6.250 -0.3139 0.02065 0.01288 -0.0895 0.9353 0.0416
-6.000 -0.2879 0.01999 0.01208 -0.0893 0.9313 0.0430
-5.750 -0.2632 0.01936 0.01132 -0.0888 0.9263 0.0439
-5.500 -0.2328 0.01847 0.01038 -0.0896 0.9235 0.0450
-5.250 -0.2004 0.01775 0.00963 -0.0908 0.9215 0.0464
-4.750 -0.1459 0.01679 0.00860 -0.0908 0.9132 0.0498
-4.500 -0.1165 0.01635 0.00811 -0.0912 0.9094 0.0524
-4.250 -0.0846 0.01585 0.00756 -0.0920 0.9068 0.0549
-4.000 -0.0517 0.01532 0.00703 -0.0932 0.9047 0.0586
-3.750 -0.0304 0.01505 0.00673 -0.0919 0.8975 0.0626
-3.500 -0.0003 0.01464 0.00630 -0.0924 0.8938 0.0693
-3.250 0.0322 0.01424 0.00589 -0.0933 0.8910 0.0800
-3.000 0.0573 0.01392 0.00563 -0.0928 0.8851 0.0955
-2.750 0.0854 0.01355 0.00538 -0.0930 0.8802 0.1236
-2.500 0.1171 0.01312 0.00509 -0.0939 0.8769 0.1642
-2.250 0.1430 0.01277 0.00492 -0.0936 0.8709 0.2125
-2.000 0.1700 0.01229 0.00478 -0.0937 0.8654 0.3023
-1.750 0.2005 0.01177 0.00460 -0.0944 0.8617 0.4022
-1.500 0.2241 0.01146 0.00456 -0.0935 0.8544 0.4755
-1.250 0.2527 0.01111 0.00442 -0.0936 0.8491 0.5411
-1.000 0.2792 0.01074 0.00434 -0.0931 0.8435 0.6279
-0.750 0.3023 0.01038 0.00436 -0.0917 0.8364 0.7361
-0.500 0.3337 0.01010 0.00434 -0.0915 0.8319 0.8449
-0.250 0.3735 0.01010 0.00441 -0.0935 0.8249 0.9223
0.000 0.4240 0.01005 0.00432 -0.0981 0.8194 0.9674
0.250 0.4707 0.01001 0.00420 -0.1020 0.8099 0.9889
0.500 0.5160 0.00992 0.00402 -0.1056 0.7982 1.0000
0.750 0.5424 0.00988 0.00388 -0.1052 0.7862 1.0000
1.000 0.5657 0.00992 0.00385 -0.1043 0.7744 1.0000
1.250 0.5899 0.00995 0.00383 -0.1035 0.7630 1.0000
1.500 0.6149 0.00999 0.00381 -0.1028 0.7516 1.0000
1.750 0.6400 0.01004 0.00379 -0.1022 0.7397 1.0000
2.000 0.6638 0.01012 0.00381 -0.1013 0.7267 1.0000
2.250 0.6875 0.01020 0.00384 -0.1003 0.7123 1.0000
2.500 0.7111 0.01030 0.00384 -0.0993 0.6944 1.0000
2.750 0.7334 0.01043 0.00389 -0.0981 0.6739 1.0000
3.000 0.7561 0.01057 0.00395 -0.0969 0.6545 1.0000
3.250 0.7790 0.01073 0.00404 -0.0959 0.6374 1.0000
3.500 0.8017 0.01091 0.00416 -0.0948 0.6198 1.0000
3.750 0.8240 0.01111 0.00429 -0.0936 0.6011 1.0000
4.000 0.8460 0.01132 0.00444 -0.0924 0.5820 1.0000
4.250 0.8678 0.01155 0.00462 -0.0911 0.5624 1.0000
4.500 0.8888 0.01182 0.00481 -0.0898 0.5410 1.0000
4.750 0.9093 0.01210 0.00502 -0.0883 0.5171 1.0000
5.000 0.9292 0.01242 0.00525 -0.0867 0.4932 1.0000
5.250 0.9480 0.01278 0.00552 -0.0850 0.4658 1.0000
5.500 0.9649 0.01322 0.00581 -0.0829 0.4325 1.0000
5.750 0.9809 0.01371 0.00615 -0.0808 0.3975 1.0000
6.000 0.9972 0.01422 0.00651 -0.0787 0.3678 1.0000
6.250 1.0145 0.01470 0.00692 -0.0769 0.3443 1.0000
6.500 1.0323 0.01517 0.00732 -0.0751 0.3239 1.0000
6.750 1.0500 0.01565 0.00775 -0.0734 0.3037 1.0000
7.000 1.0667 0.01615 0.00819 -0.0715 0.2847 1.0000
7.250 1.0832 0.01664 0.00867 -0.0696 0.2675 1.0000
7.750 1.1162 0.01770 0.00966 -0.0660 0.2331 1.0000
8.000 1.1319 0.01829 0.01021 -0.0641 0.2142 1.0000
8.250 1.1464 0.01897 0.01081 -0.0621 0.1946 1.0000
8.500 1.1604 0.01969 0.01147 -0.0601 0.1752 1.0000
8.750 1.1748 0.02041 0.01213 -0.0583 0.1564 1.0000
9.000 1.1891 0.02116 0.01283 -0.0564 0.1384 1.0000
9.250 1.2033 0.02193 0.01356 -0.0546 0.1222 1.0000
9.500 1.2167 0.02275 0.01434 -0.0528 0.1062 1.0000
9.750 1.2293 0.02366 0.01521 -0.0509 0.0914 1.0000
10.000 1.2411 0.02463 0.01616 -0.0489 0.0783 1.0000
10.250 1.2521 0.02568 0.01719 -0.0469 0.0642 1.0000
10.500 1.2610 0.02690 0.01835 -0.0448 0.0490 1.0000
10.750 1.2688 0.02824 0.01964 -0.0426 0.0376 1.0000
11.000 1.2760 0.02964 0.02104 -0.0404 0.0310 1.0000
11.250 1.2836 0.03104 0.02251 -0.0384 0.0270 1.0000
11.500 1.2902 0.03254 0.02407 -0.0364 0.0244 1.0000
11.750 1.2973 0.03401 0.02566 -0.0346 0.0224 1.0000
12.000 1.3023 0.03570 0.02743 -0.0328 0.0209 1.0000
12.250 1.3045 0.03767 0.02949 -0.0309 0.0198 1.0000
12.500 1.3089 0.03950 0.03147 -0.0293 0.0191 1.0000
12.750 1.3120 0.04151 0.03362 -0.0278 0.0183 1.0000
13.000 1.3140 0.04368 0.03591 -0.0264 0.0176 1.0000
13.250 1.3150 0.04601 0.03839 -0.0252 0.0170 1.0000
13.500 1.3148 0.04855 0.04105 -0.0242 0.0164 1.0000
13.750 1.3121 0.05144 0.04404 -0.0233 0.0159 1.0000
14.000 1.3063 0.05479 0.04751 -0.0226 0.0154 1.0000
14.250 1.3039 0.05792 0.05077 -0.0222 0.0150 1.0000
14.500 1.3022 0.06109 0.05408 -0.0220 0.0147 1.0000
14.750 1.2991 0.06450 0.05765 -0.0220 0.0144 1.0000
15.000 1.2954 0.06810 0.06140 -0.0221 0.0141 1.0000
15.250 1.2911 0.07190 0.06533 -0.0225 0.0138 1.0000
15.500 1.2864 0.07584 0.06942 -0.0231 0.0136 1.0000
15.750 1.2813 0.07993 0.07364 -0.0238 0.0134 1.0000
16.000 1.2757 0.08419 0.07804 -0.0247 0.0132 1.0000
16.250 1.2700 0.08859 0.08257 -0.0259 0.0130 1.0000
16.500 1.2639 0.09313 0.08724 -0.0272 0.0128 1.0000
16.750 1.2576 0.09778 0.09204 -0.0287 0.0126 1.0000
17.000 1.2511 0.10253 0.09691 -0.0304 0.0124 1.0000
17.250 1.2446 0.10739 0.10187 -0.0323 0.0122 1.0000
17.500 1.2380 0.11234 0.10694 -0.0343 0.0121 1.0000
17.750 1.2315 0.11733 0.11203 -0.0364 0.0119 1.0000
18.000 1.2250 0.12226 0.11706 -0.0385 0.0117 1.0000
18.250 1.2178 0.12747 0.12237 -0.0409 0.0115 1.0000
18.500 1.2095 0.13337 0.12844 -0.0441 0.0114 1.0000
18.750 1.2005 0.13954 0.13479 -0.0476 0.0113 1.0000
19.000 1.1911 0.14597 0.14138 -0.0514 0.0112 1.0000
19.250 1.1811 0.15271 0.14829 -0.0555 0.0112 1.0000
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