NACA 2.5411 (naca2411-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2.5411 (naca2411-il) Reynolds number: 200,000 Max Cl/Cd: 67.44 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2411-il-200000-n5.txt Download as CSV file: xf-naca2411-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2.5411
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7077 0.05268 0.04846 -0.0688 1.0000 0.0234
-11.250 -0.7537 0.04585 0.04137 -0.0716 1.0000 0.0231
-11.000 -0.7810 0.04303 0.03838 -0.0678 1.0000 0.0231
-10.750 -0.7946 0.04047 0.03562 -0.0647 1.0000 0.0233
-10.500 -0.8032 0.03809 0.03302 -0.0616 1.0000 0.0235
-10.250 -0.8067 0.03595 0.03065 -0.0585 1.0000 0.0238
-10.000 -0.8069 0.03392 0.02836 -0.0555 1.0000 0.0242
-9.750 -0.8041 0.03201 0.02620 -0.0527 1.0000 0.0246
-9.500 -0.7984 0.03026 0.02417 -0.0501 1.0000 0.0251
-9.250 -0.7903 0.02865 0.02229 -0.0476 1.0000 0.0256
-9.000 -0.7789 0.02725 0.02057 -0.0454 0.9998 0.0263
-8.750 -0.7511 0.02593 0.01918 -0.0466 0.9968 0.0271
-8.500 -0.7214 0.02496 0.01812 -0.0479 0.9938 0.0281
-8.250 -0.6936 0.02387 0.01687 -0.0486 0.9902 0.0291
-8.000 -0.6645 0.02271 0.01551 -0.0495 0.9867 0.0301
-7.750 -0.6334 0.02164 0.01421 -0.0507 0.9838 0.0314
-7.500 -0.6065 0.02067 0.01317 -0.0511 0.9794 0.0325
-7.250 -0.5766 0.01999 0.01245 -0.0519 0.9753 0.0342
-7.000 -0.5442 0.01931 0.01166 -0.0532 0.9722 0.0364
-6.750 -0.5153 0.01857 0.01080 -0.0537 0.9679 0.0385
-6.500 -0.4867 0.01790 0.01012 -0.0542 0.9629 0.0406
-6.250 -0.4539 0.01732 0.00946 -0.0554 0.9594 0.0437
-6.000 -0.4195 0.01671 0.00880 -0.0569 0.9567 0.0475
-5.750 -0.3940 0.01626 0.00832 -0.0566 0.9496 0.0515
-5.500 -0.3611 0.01572 0.00774 -0.0577 0.9455 0.0563
-5.250 -0.3249 0.01525 0.00724 -0.0595 0.9426 0.0627
-5.000 -0.2984 0.01482 0.00682 -0.0592 0.9350 0.0693
-4.750 -0.2646 0.01440 0.00638 -0.0605 0.9303 0.0780
-4.500 -0.2289 0.01399 0.00595 -0.0621 0.9268 0.0885
-4.250 -0.2042 0.01364 0.00565 -0.0614 0.9181 0.0991
-4.000 -0.1709 0.01326 0.00529 -0.0625 0.9132 0.1135
-3.750 -0.1427 0.01295 0.00502 -0.0626 0.9058 0.1292
-3.500 -0.1121 0.01261 0.00474 -0.0631 0.8990 0.1487
-3.250 -0.0821 0.01230 0.00449 -0.0635 0.8919 0.1715
-3.000 -0.0528 0.01200 0.00427 -0.0637 0.8836 0.1966
-2.750 -0.0235 0.01173 0.00407 -0.0639 0.8753 0.2247
-2.500 0.0063 0.01145 0.00387 -0.0642 0.8667 0.2564
-2.250 0.0338 0.01118 0.00371 -0.0641 0.8564 0.2911
-2.000 0.0631 0.01090 0.00354 -0.0643 0.8471 0.3317
-1.750 0.0899 0.01062 0.00339 -0.0639 0.8358 0.3766
-1.500 0.1155 0.01031 0.00328 -0.0633 0.8239 0.4352
-1.250 0.1405 0.00997 0.00320 -0.0626 0.8121 0.5134
-1.000 0.1650 0.00966 0.00314 -0.0616 0.7998 0.5970
-0.750 0.1890 0.00939 0.00311 -0.0604 0.7867 0.6771
-0.500 0.2140 0.00917 0.00312 -0.0592 0.7729 0.7550
-0.250 0.2457 0.00906 0.00315 -0.0593 0.7590 0.8286
0.000 0.2893 0.00907 0.00319 -0.0620 0.7445 0.8882
0.250 0.3336 0.00913 0.00320 -0.0651 0.7291 0.9249
0.500 0.3755 0.00922 0.00319 -0.0678 0.7129 0.9480
0.750 0.4149 0.00932 0.00319 -0.0700 0.6962 0.9651
1.000 0.4533 0.00943 0.00320 -0.0721 0.6791 0.9792
1.250 0.4928 0.00953 0.00320 -0.0745 0.6614 0.9909
1.500 0.5320 0.00965 0.00321 -0.0769 0.6440 1.0000
1.750 0.5534 0.00977 0.00324 -0.0756 0.6280 1.0000
2.000 0.5749 0.00990 0.00329 -0.0742 0.6122 1.0000
2.250 0.5965 0.01004 0.00336 -0.0729 0.5966 1.0000
2.500 0.6182 0.01020 0.00344 -0.0716 0.5812 1.0000
2.750 0.6399 0.01036 0.00354 -0.0702 0.5660 1.0000
3.000 0.6616 0.01053 0.00366 -0.0689 0.5508 1.0000
3.250 0.6833 0.01072 0.00379 -0.0676 0.5354 1.0000
3.500 0.7050 0.01091 0.00393 -0.0663 0.5202 1.0000
3.750 0.7266 0.01111 0.00409 -0.0650 0.5045 1.0000
4.000 0.7479 0.01133 0.00425 -0.0636 0.4879 1.0000
4.250 0.7689 0.01156 0.00443 -0.0621 0.4704 1.0000
4.500 0.7898 0.01179 0.00461 -0.0607 0.4514 1.0000
4.750 0.8105 0.01204 0.00482 -0.0592 0.4311 1.0000
5.000 0.8303 0.01233 0.00503 -0.0576 0.4083 1.0000
5.250 0.8504 0.01261 0.00526 -0.0561 0.3839 1.0000
5.500 0.8695 0.01295 0.00552 -0.0544 0.3573 1.0000
5.750 0.8882 0.01333 0.00580 -0.0526 0.3297 1.0000
6.000 0.9063 0.01377 0.00611 -0.0508 0.2989 1.0000
6.250 0.9236 0.01427 0.00648 -0.0490 0.2658 1.0000
6.500 0.9401 0.01485 0.00690 -0.0470 0.2312 1.0000
6.750 0.9562 0.01547 0.00737 -0.0451 0.1981 1.0000
7.000 0.9721 0.01613 0.00788 -0.0431 0.1677 1.0000
7.250 0.9878 0.01681 0.00842 -0.0412 0.1403 1.0000
7.500 1.0035 0.01749 0.00900 -0.0392 0.1179 1.0000
7.750 1.0188 0.01818 0.00960 -0.0373 0.0995 1.0000
8.000 1.0339 0.01886 0.01023 -0.0353 0.0855 1.0000
8.250 1.0490 0.01953 0.01086 -0.0333 0.0744 1.0000
8.500 1.0633 0.02018 0.01151 -0.0311 0.0660 1.0000
8.750 1.0756 0.02087 0.01221 -0.0287 0.0596 1.0000
9.000 1.0882 0.02155 0.01291 -0.0263 0.0542 1.0000
9.250 1.0992 0.02232 0.01370 -0.0238 0.0500 1.0000
9.500 1.1114 0.02305 0.01450 -0.0215 0.0463 1.0000
9.750 1.1205 0.02398 0.01543 -0.0190 0.0431 1.0000
10.000 1.1320 0.02479 0.01633 -0.0169 0.0403 1.0000
10.250 1.1424 0.02569 0.01730 -0.0147 0.0378 1.0000
10.500 1.1501 0.02679 0.01843 -0.0124 0.0360 1.0000
10.750 1.1578 0.02793 0.01965 -0.0102 0.0343 1.0000
11.000 1.1663 0.02907 0.02090 -0.0083 0.0329 1.0000
11.250 1.1740 0.03030 0.02221 -0.0064 0.0314 1.0000
11.500 1.1806 0.03165 0.02361 -0.0047 0.0301 1.0000
11.750 1.1844 0.03328 0.02528 -0.0029 0.0290 1.0000
12.000 1.1911 0.03478 0.02691 -0.0014 0.0281 1.0000
12.250 1.1973 0.03635 0.02860 -0.0001 0.0271 1.0000
12.500 1.2024 0.03810 0.03044 0.0011 0.0262 1.0000
12.750 1.2068 0.03996 0.03240 0.0022 0.0256 1.0000
13.000 1.2107 0.04192 0.03445 0.0031 0.0251 1.0000
13.250 1.2132 0.04410 0.03670 0.0039 0.0245 1.0000
13.500 1.2140 0.04653 0.03918 0.0045 0.0240 1.0000
13.750 1.2173 0.04882 0.04161 0.0051 0.0236 1.0000
14.000 1.2198 0.05126 0.04422 0.0054 0.0231 1.0000
14.250 1.2213 0.05387 0.04697 0.0057 0.0226 1.0000
14.500 1.2222 0.05661 0.04985 0.0057 0.0222 1.0000
14.750 1.2220 0.05955 0.05294 0.0055 0.0217 1.0000
15.000 1.2211 0.06263 0.05615 0.0050 0.0212 1.0000
15.250 1.2193 0.06596 0.05959 0.0044 0.0208 1.0000
15.500 1.2174 0.06937 0.06310 0.0035 0.0205 1.0000
15.750 1.2146 0.07299 0.06684 0.0025 0.0202 1.0000
16.000 1.2114 0.07673 0.07066 0.0014 0.0199 1.0000
16.250 1.2076 0.08068 0.07471 0.0002 0.0197 1.0000
16.500 1.2019 0.08506 0.07922 -0.0014 0.0195 1.0000
16.750 1.1927 0.09022 0.08458 -0.0035 0.0194 1.0000
17.000 1.1819 0.09584 0.09041 -0.0061 0.0192 1.0000
17.250 1.1697 0.10193 0.09670 -0.0092 0.0191 1.0000
17.500 1.1551 0.10868 0.10365 -0.0127 0.0190 1.0000
17.750 1.1387 0.11607 0.11125 -0.0169 0.0189 1.0000
18.000 1.1207 0.12411 0.11949 -0.0216 0.0189 1.0000
18.250 1.0999 0.13317 0.12874 -0.0271 0.0189 1.0000
18.500 1.0707 0.14482 0.14061 -0.0344 0.0190 1.0000
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