CLARK V AIRFOIL (clarkv-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: CLARK V AIRFOIL (clarkv-il) Reynolds number: 100,000 Max Cl/Cd: 57.62 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-clarkv-il-100000.txt Download as CSV file: xf-clarkv-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4133 0.10727 0.10230 -0.0359 1.0000 0.1235
-9.000 -0.4513 0.10618 0.10138 -0.0370 1.0000 0.1252
-8.750 -0.4867 0.10483 0.10017 -0.0364 1.0000 0.1255
-8.500 -0.4308 0.09894 0.09416 -0.0321 1.0000 0.1304
-8.250 -0.4359 0.09678 0.09205 -0.0302 1.0000 0.1339
-8.000 -0.4562 0.09491 0.09028 -0.0286 1.0000 0.1372
-7.750 -0.4932 0.09338 0.08890 -0.0275 1.0000 0.1391
-7.250 -0.5171 0.08654 0.08217 -0.0266 1.0000 0.1434
-7.000 -0.5104 0.08469 0.08034 -0.0230 1.0000 0.1479
-6.750 -0.5549 0.07987 0.07528 -0.0331 1.0000 0.1564
-6.500 -0.5349 0.07700 0.07265 -0.0261 1.0000 0.1590
-6.250 -0.5276 0.07528 0.07095 -0.0228 1.0000 0.1647
-6.000 -0.5350 0.07064 0.06620 -0.0262 1.0000 0.1743
-5.750 -0.5265 0.06862 0.06423 -0.0234 1.0000 0.1792
-5.500 -0.5238 0.06474 0.06022 -0.0253 1.0000 0.1908
-5.250 -0.4982 0.04557 0.03936 -0.0389 1.0000 0.1130
-5.000 -0.4853 0.04648 0.04063 -0.0370 1.0000 0.1307
-4.750 -0.4509 0.03694 0.02915 -0.0395 1.0000 0.0963
-4.500 -0.4283 0.03428 0.02617 -0.0395 1.0000 0.0955
-4.250 -0.4050 0.03259 0.02402 -0.0392 1.0000 0.0963
-4.000 -0.3817 0.03055 0.02175 -0.0392 1.0000 0.0984
-3.750 -0.3583 0.02925 0.02024 -0.0389 1.0000 0.1000
-3.500 -0.3254 0.02816 0.01896 -0.0403 0.9977 0.1023
-3.250 -0.2821 0.02739 0.01795 -0.0435 0.9930 0.1073
-3.000 -0.2418 0.02656 0.01697 -0.0461 0.9875 0.1136
-2.750 -0.1986 0.02605 0.01644 -0.0493 0.9831 0.1220
-2.500 -0.1631 0.02539 0.01586 -0.0512 0.9765 0.1338
-2.250 -0.1201 0.02485 0.01546 -0.0544 0.9719 0.1602
-2.000 -0.0862 0.02398 0.01502 -0.0562 0.9655 0.2206
-1.750 -0.0493 0.02254 0.01516 -0.0585 0.9612 0.5217
-1.500 -0.0204 0.02189 0.01577 -0.0564 0.9574 0.8741
-1.250 0.0180 0.02198 0.01566 -0.0591 0.9472 1.0000
-1.000 0.0562 0.02238 0.01576 -0.0617 0.9401 1.0000
-0.750 0.0910 0.02270 0.01586 -0.0636 0.9319 1.0000
-0.500 0.1247 0.02303 0.01601 -0.0652 0.9238 1.0000
-0.250 0.1627 0.02333 0.01613 -0.0676 0.9163 1.0000
0.000 0.1924 0.02363 0.01630 -0.0684 0.9071 1.0000
0.250 0.2343 0.02387 0.01640 -0.0713 0.9007 1.0000
0.500 0.2611 0.02413 0.01657 -0.0715 0.8903 1.0000
0.750 0.3077 0.02422 0.01656 -0.0751 0.8849 1.0000
1.000 0.3334 0.02440 0.01667 -0.0749 0.8732 1.0000
1.250 0.3659 0.02448 0.01670 -0.0758 0.8631 1.0000
1.500 0.4118 0.02426 0.01643 -0.0788 0.8563 1.0000
1.750 0.4393 0.02434 0.01648 -0.0787 0.8448 1.0000
2.000 0.4891 0.02392 0.01604 -0.0821 0.8402 1.0000
2.250 0.5132 0.02402 0.01615 -0.0814 0.8280 1.0000
2.500 0.5436 0.02398 0.01611 -0.0816 0.8178 1.0000
2.750 0.5898 0.02337 0.01553 -0.0842 0.8121 1.0000
3.000 0.6186 0.02324 0.01543 -0.0839 0.8011 1.0000
3.250 0.6696 0.02229 0.01454 -0.0870 0.7962 1.0000
3.500 0.6995 0.02197 0.01427 -0.0866 0.7842 1.0000
3.750 0.7389 0.02120 0.01354 -0.0876 0.7739 1.0000
4.000 0.7875 0.02006 0.01248 -0.0898 0.7651 1.0000
4.250 0.8196 0.01959 0.01206 -0.0897 0.7511 1.0000
4.500 0.8523 0.01916 0.01168 -0.0897 0.7367 1.0000
4.750 0.8856 0.01874 0.01132 -0.0897 0.7212 1.0000
5.000 0.9191 0.01835 0.01096 -0.0899 0.7043 1.0000
5.250 0.9458 0.01820 0.01084 -0.0889 0.6839 1.0000
5.500 0.9731 0.01807 0.01074 -0.0880 0.6615 1.0000
5.750 0.9993 0.01802 0.01067 -0.0870 0.6369 1.0000
6.000 1.0246 0.01803 0.01062 -0.0858 0.6091 1.0000
6.250 1.0454 0.01819 0.01071 -0.0838 0.5774 1.0000
6.500 1.0637 0.01846 0.01091 -0.0815 0.5431 1.0000
6.750 1.0812 0.01884 0.01117 -0.0792 0.5085 1.0000
7.000 1.0982 0.01934 0.01152 -0.0769 0.4747 1.0000
7.250 1.1144 0.01996 0.01197 -0.0746 0.4422 1.0000
7.500 1.1298 0.02066 0.01253 -0.0722 0.4111 1.0000
7.750 1.1448 0.02144 0.01319 -0.0699 0.3819 1.0000
8.000 1.1596 0.02227 0.01393 -0.0677 0.3547 1.0000
8.250 1.1752 0.02317 0.01471 -0.0656 0.3301 1.0000
8.500 1.1895 0.02406 0.01553 -0.0634 0.3068 1.0000
8.750 1.2006 0.02491 0.01634 -0.0607 0.2837 1.0000
9.000 1.2080 0.02568 0.01706 -0.0575 0.2614 1.0000
9.250 1.2130 0.02646 0.01781 -0.0539 0.2404 1.0000
9.500 1.2180 0.02732 0.01867 -0.0504 0.2199 1.0000
9.750 1.2238 0.02833 0.01965 -0.0473 0.2011 1.0000
10.000 1.2289 0.02947 0.02078 -0.0442 0.1818 1.0000
10.250 1.2319 0.03074 0.02206 -0.0411 0.1614 1.0000
10.500 1.2322 0.03231 0.02352 -0.0378 0.1410 1.0000
10.750 1.2305 0.03409 0.02529 -0.0345 0.1180 1.0000
11.000 1.2287 0.03627 0.02731 -0.0314 0.0997 1.0000
11.250 1.2313 0.03848 0.02945 -0.0287 0.0866 1.0000
11.500 1.2373 0.04060 0.03144 -0.0267 0.0774 1.0000
11.750 1.2462 0.04253 0.03357 -0.0247 0.0705 1.0000
12.000 1.2642 0.04473 0.03560 -0.0237 0.0651 1.0000
12.250 1.2764 0.04679 0.03795 -0.0221 0.0616 1.0000
12.500 1.2874 0.04880 0.04007 -0.0206 0.0582 1.0000
12.750 1.3097 0.05143 0.04262 -0.0203 0.0547 1.0000
13.000 1.3133 0.05398 0.04555 -0.0183 0.0532 1.0000
13.250 1.3169 0.05691 0.04880 -0.0165 0.0520 1.0000
13.500 1.3166 0.06008 0.05228 -0.0146 0.0511 1.0000
13.750 1.3121 0.06348 0.05597 -0.0128 0.0504 1.0000
14.000 1.3037 0.06708 0.05985 -0.0112 0.0499 1.0000
14.250 1.2926 0.07090 0.06394 -0.0099 0.0494 1.0000
14.500 1.2784 0.07507 0.06837 -0.0090 0.0490 1.0000
14.750 1.2601 0.07978 0.07335 -0.0086 0.0488 1.0000
15.000 1.2349 0.08545 0.07932 -0.0092 0.0490 1.0000
15.250 1.2009 0.09274 0.08694 -0.0112 0.0497 1.0000
15.500 1.1644 0.10131 0.09582 -0.0148 0.0507 1.0000
15.750 1.1273 0.11119 0.10595 -0.0202 0.0518 1.0000
16.000 1.0903 0.12244 0.11737 -0.0272 0.0530 1.0000
16.250 1.0565 0.13454 0.12958 -0.0348 0.0541 1.0000
16.500 1.0334 0.14533 0.14040 -0.0409 0.0550 1.0000
16.750 0.9473 0.18729 0.18221 -0.0645 0.0765 1.0000
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