NACA 2.5411 (naca2411-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2.5411 (naca2411-il) Reynolds number: 50,000 Max Cl/Cd: 35.91 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2411-il-50000-n5.txt Download as CSV file: xf-naca2411-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4528 0.09762 0.08989 -0.0393 1.0000 0.0677
-9.750 -0.4613 0.09263 0.08498 -0.0414 1.0000 0.0672
-9.250 -0.5225 0.07543 0.06800 -0.0527 1.0000 0.0644
-9.000 -0.5441 0.07095 0.06355 -0.0528 1.0000 0.0642
-8.750 -0.5632 0.06639 0.05895 -0.0527 1.0000 0.0641
-8.500 -0.5816 0.06184 0.05427 -0.0521 1.0000 0.0642
-8.250 -0.5981 0.05724 0.04940 -0.0508 1.0000 0.0646
-8.000 -0.5921 0.05539 0.04761 -0.0491 1.0000 0.0660
-7.750 -0.5876 0.05338 0.04555 -0.0473 1.0000 0.0678
-7.500 -0.5879 0.05030 0.04222 -0.0456 1.0000 0.0692
-7.250 -0.5869 0.04697 0.03858 -0.0439 1.0000 0.0706
-7.000 -0.5831 0.04363 0.03482 -0.0421 1.0000 0.0720
-6.750 -0.5763 0.04044 0.03110 -0.0403 1.0000 0.0742
-6.500 -0.5655 0.03796 0.02822 -0.0386 1.0000 0.0771
-6.250 -0.5509 0.03662 0.02684 -0.0371 1.0000 0.0804
-6.000 -0.5359 0.03479 0.02472 -0.0355 1.0000 0.0840
-5.750 -0.5197 0.03283 0.02221 -0.0340 1.0000 0.0888
-5.500 -0.5028 0.03176 0.02121 -0.0327 1.0000 0.0934
-5.250 -0.4845 0.03044 0.01962 -0.0313 1.0000 0.0993
-5.000 -0.4662 0.02933 0.01841 -0.0300 1.0000 0.1057
-4.750 -0.4472 0.02836 0.01725 -0.0287 1.0000 0.1136
-4.500 -0.4282 0.02752 0.01638 -0.0275 1.0000 0.1220
-4.250 -0.4083 0.02672 0.01543 -0.0263 1.0000 0.1324
-4.000 -0.3888 0.02609 0.01473 -0.0251 1.0000 0.1447
-3.750 -0.3693 0.02550 0.01414 -0.0240 1.0000 0.1580
-3.500 -0.3352 0.02494 0.01359 -0.0257 0.9944 0.1792
-3.000 -0.2607 0.02398 0.01272 -0.0303 0.9783 0.2417
-2.750 -0.2225 0.02357 0.01242 -0.0328 0.9705 0.2863
-2.500 -0.1890 0.02308 0.01215 -0.0344 0.9609 0.3381
-2.250 -0.1555 0.02257 0.01194 -0.0358 0.9517 0.4050
-2.000 -0.1220 0.02201 0.01188 -0.0369 0.9432 0.5023
-1.750 -0.0956 0.02145 0.01189 -0.0361 0.9329 0.6322
-1.500 -0.0424 0.02107 0.01210 -0.0391 0.9282 0.8402
-1.250 0.0510 0.02115 0.01194 -0.0516 0.9272 1.0000
-1.000 0.0825 0.02119 0.01174 -0.0528 0.9145 1.0000
-0.750 0.1151 0.02125 0.01158 -0.0541 0.9023 1.0000
-0.500 0.1508 0.02130 0.01145 -0.0559 0.8914 1.0000
-0.250 0.1895 0.02131 0.01130 -0.0580 0.8812 1.0000
0.000 0.2200 0.02137 0.01122 -0.0586 0.8684 1.0000
0.250 0.2519 0.02141 0.01115 -0.0594 0.8561 1.0000
0.500 0.2857 0.02140 0.01105 -0.0604 0.8448 1.0000
0.750 0.3209 0.02137 0.01093 -0.0616 0.8338 1.0000
1.000 0.3486 0.02144 0.01094 -0.0614 0.8202 1.0000
1.500 0.4064 0.02156 0.01097 -0.0613 0.7940 1.0000
1.750 0.4373 0.02158 0.01096 -0.0616 0.7816 1.0000
2.000 0.4707 0.02154 0.01090 -0.0621 0.7701 1.0000
2.250 0.4969 0.02166 0.01101 -0.0615 0.7559 1.0000
2.500 0.5233 0.02179 0.01113 -0.0609 0.7417 1.0000
2.750 0.5499 0.02192 0.01127 -0.0603 0.7275 1.0000
3.000 0.5766 0.02206 0.01142 -0.0597 0.7135 1.0000
3.250 0.6034 0.02220 0.01158 -0.0592 0.6993 1.0000
3.500 0.6302 0.02236 0.01176 -0.0585 0.6851 1.0000
3.750 0.6568 0.02252 0.01195 -0.0579 0.6707 1.0000
4.000 0.6831 0.02270 0.01215 -0.0571 0.6559 1.0000
4.250 0.7087 0.02290 0.01241 -0.0563 0.6407 1.0000
4.500 0.7336 0.02312 0.01267 -0.0553 0.6250 1.0000
4.750 0.7576 0.02337 0.01297 -0.0542 0.6086 1.0000
5.000 0.7809 0.02364 0.01332 -0.0530 0.5914 1.0000
5.250 0.8038 0.02391 0.01365 -0.0516 0.5736 1.0000
5.500 0.8265 0.02418 0.01397 -0.0502 0.5549 1.0000
5.750 0.8494 0.02441 0.01423 -0.0488 0.5353 1.0000
6.000 0.8697 0.02471 0.01460 -0.0470 0.5140 1.0000
6.250 0.8884 0.02503 0.01497 -0.0450 0.4908 1.0000
6.500 0.9066 0.02535 0.01530 -0.0429 0.4663 1.0000
6.750 0.9230 0.02570 0.01568 -0.0406 0.4399 1.0000
7.000 0.9368 0.02615 0.01617 -0.0380 0.4111 1.0000
7.250 0.9496 0.02665 0.01665 -0.0352 0.3802 1.0000
7.500 0.9608 0.02724 0.01718 -0.0324 0.3473 1.0000
7.750 0.9701 0.02798 0.01783 -0.0294 0.3124 1.0000
8.000 0.9776 0.02891 0.01866 -0.0264 0.2767 1.0000
8.250 0.9835 0.03005 0.01962 -0.0234 0.2430 1.0000
8.500 0.9870 0.03135 0.02075 -0.0202 0.2130 1.0000
8.750 0.9904 0.03282 0.02207 -0.0172 0.1876 1.0000
9.000 0.9932 0.03443 0.02353 -0.0145 0.1671 1.0000
9.250 0.9973 0.03612 0.02511 -0.0120 0.1499 1.0000
9.500 1.0025 0.03785 0.02681 -0.0098 0.1359 1.0000
9.750 1.0082 0.03962 0.02855 -0.0079 0.1240 1.0000
10.000 1.0168 0.04137 0.03037 -0.0062 0.1135 1.0000
10.250 1.0254 0.04318 0.03223 -0.0046 0.1049 1.0000
10.500 1.0350 0.04499 0.03402 -0.0032 0.0979 1.0000
10.750 1.0466 0.04687 0.03608 -0.0019 0.0909 1.0000
11.000 1.0572 0.04872 0.03795 -0.0007 0.0854 1.0000
11.250 1.0699 0.05082 0.04025 0.0004 0.0804 1.0000
11.500 1.0787 0.05298 0.04258 0.0015 0.0760 1.0000
11.750 1.0926 0.05492 0.04444 0.0023 0.0723 1.0000
12.000 1.0973 0.05778 0.04767 0.0034 0.0696 1.0000
12.250 1.0983 0.06075 0.05094 0.0043 0.0671 1.0000
12.500 1.0983 0.06370 0.05410 0.0050 0.0648 1.0000
12.750 1.1001 0.06650 0.05700 0.0055 0.0628 1.0000
13.000 1.1061 0.06937 0.05990 0.0059 0.0612 1.0000
13.250 1.0925 0.07392 0.06480 0.0057 0.0606 1.0000
13.500 1.0753 0.07910 0.07029 0.0047 0.0601 1.0000
13.750 1.0554 0.08494 0.07641 0.0029 0.0599 1.0000
14.000 1.0313 0.09180 0.08352 -0.0001 0.0598 1.0000
14.250 1.0039 0.09983 0.09178 -0.0043 0.0600 1.0000
14.500 0.9741 0.10920 0.10131 -0.0097 0.0603 1.0000
14.750 0.9410 0.12054 0.11276 -0.0166 0.0607 1.0000
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Polar data table (+)
Polar graphs
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