NACA 2.5411 (naca2411-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2.5411 (naca2411-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.73 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2411-il-1000000.txt Download as CSV file: xf-naca2411-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -0.7712 0.09876 0.09662 -0.0387 1.0000 0.0146
-15.250 -0.8289 0.08407 0.08178 -0.0474 1.0000 0.0144
-15.000 -0.8872 0.07008 0.06763 -0.0562 1.0000 0.0143
-14.750 -0.9347 0.05805 0.05543 -0.0644 1.0000 0.0142
-14.500 -0.9636 0.04839 0.04558 -0.0723 1.0000 0.0142
-14.250 -0.9775 0.04183 0.03885 -0.0783 1.0000 0.0142
-14.000 -0.9934 0.03672 0.03356 -0.0821 1.0000 0.0142
-13.750 -1.0053 0.03363 0.03033 -0.0824 1.0000 0.0143
-13.500 -1.0123 0.03185 0.02844 -0.0804 1.0000 0.0143
-13.250 -1.0213 0.03063 0.02711 -0.0764 1.0000 0.0144
-13.000 -1.0286 0.02954 0.02593 -0.0720 1.0000 0.0145
-12.750 -1.0328 0.02810 0.02435 -0.0682 1.0000 0.0146
-12.500 -1.0465 0.02584 0.02190 -0.0632 1.0000 0.0148
-12.250 -1.0472 0.02441 0.02035 -0.0594 1.0000 0.0150
-12.000 -1.0420 0.02335 0.01920 -0.0563 1.0000 0.0152
-11.750 -1.0331 0.02252 0.01830 -0.0536 1.0000 0.0154
-11.500 -1.0066 0.02162 0.01733 -0.0543 0.9988 0.0158
-11.250 -0.9771 0.02094 0.01658 -0.0555 0.9974 0.0161
-11.000 -0.9477 0.02016 0.01572 -0.0566 0.9958 0.0165
-10.750 -0.9175 0.01939 0.01485 -0.0578 0.9946 0.0170
-10.500 -0.8891 0.01861 0.01397 -0.0585 0.9929 0.0173
-10.250 -0.8608 0.01794 0.01320 -0.0591 0.9907 0.0176
-10.000 -0.8307 0.01737 0.01255 -0.0600 0.9887 0.0178
-9.750 -0.8040 0.01598 0.01102 -0.0608 0.9867 0.0184
-9.500 -0.7730 0.01522 0.01021 -0.0619 0.9853 0.0190
-9.250 -0.7402 0.01469 0.00965 -0.0633 0.9842 0.0195
-9.000 -0.7067 0.01421 0.00912 -0.0648 0.9834 0.0202
-8.750 -0.6822 0.01378 0.00864 -0.0643 0.9791 0.0207
-8.500 -0.6513 0.01332 0.00812 -0.0651 0.9768 0.0213
-8.250 -0.6184 0.01295 0.00770 -0.0662 0.9752 0.0217
-8.000 -0.5871 0.01211 0.00679 -0.0673 0.9736 0.0228
-7.750 -0.5530 0.01164 0.00631 -0.0688 0.9725 0.0239
-7.500 -0.5172 0.01126 0.00590 -0.0706 0.9716 0.0250
-7.250 -0.4878 0.01095 0.00556 -0.0709 0.9677 0.0260
-7.000 -0.4582 0.01046 0.00503 -0.0713 0.9635 0.0276
-6.750 -0.4261 0.01009 0.00466 -0.0723 0.9605 0.0297
-6.500 -0.3929 0.00981 0.00435 -0.0734 0.9580 0.0315
-6.250 -0.3663 0.00943 0.00398 -0.0731 0.9527 0.0349
-6.000 -0.3380 0.00921 0.00374 -0.0731 0.9472 0.0377
-5.750 -0.3072 0.00887 0.00341 -0.0737 0.9430 0.0424
-5.500 -0.2809 0.00870 0.00323 -0.0733 0.9361 0.0460
-5.250 -0.2529 0.00843 0.00298 -0.0733 0.9296 0.0521
-5.000 -0.2255 0.00823 0.00277 -0.0731 0.9227 0.0574
-4.750 -0.1984 0.00804 0.00258 -0.0728 0.9148 0.0636
-4.500 -0.1714 0.00784 0.00240 -0.0725 0.9069 0.0715
-4.250 -0.1444 0.00768 0.00223 -0.0722 0.8982 0.0803
-4.000 -0.1180 0.00751 0.00209 -0.0718 0.8890 0.0911
-3.750 -0.0911 0.00735 0.00194 -0.0715 0.8798 0.1047
-3.500 -0.0653 0.00718 0.00182 -0.0710 0.8690 0.1215
-3.250 -0.0391 0.00703 0.00170 -0.0705 0.8585 0.1401
-3.000 -0.0129 0.00690 0.00159 -0.0700 0.8474 0.1597
-2.750 0.0130 0.00677 0.00150 -0.0695 0.8352 0.1809
-2.500 0.0388 0.00665 0.00142 -0.0690 0.8227 0.2053
-2.250 0.0645 0.00653 0.00135 -0.0684 0.8099 0.2315
-2.000 0.0902 0.00643 0.00128 -0.0679 0.7967 0.2594
-1.750 0.1157 0.00634 0.00123 -0.0673 0.7828 0.2896
-1.500 0.1409 0.00624 0.00118 -0.0666 0.7680 0.3229
-1.250 0.1660 0.00615 0.00114 -0.0660 0.7531 0.3596
-1.000 0.1906 0.00601 0.00111 -0.0652 0.7378 0.4087
-0.750 0.2142 0.00583 0.00109 -0.0643 0.7218 0.4812
-0.500 0.2375 0.00564 0.00109 -0.0633 0.7057 0.5581
-0.250 0.2607 0.00550 0.00110 -0.0622 0.6893 0.6271
0.000 0.2835 0.00538 0.00112 -0.0610 0.6729 0.6931
0.250 0.3057 0.00526 0.00115 -0.0596 0.6564 0.7592
0.500 0.3278 0.00516 0.00119 -0.0581 0.6405 0.8217
0.750 0.3514 0.00510 0.00126 -0.0569 0.6242 0.8827
1.000 0.3830 0.00514 0.00135 -0.0574 0.6073 0.9289
1.250 0.4216 0.00527 0.00143 -0.0597 0.5899 0.9538
1.500 0.4613 0.00542 0.00151 -0.0622 0.5720 0.9667
1.750 0.4996 0.00558 0.00159 -0.0644 0.5551 0.9748
2.000 0.5329 0.00574 0.00168 -0.0655 0.5391 0.9824
2.250 0.5711 0.00588 0.00175 -0.0677 0.5227 0.9863
2.500 0.6080 0.00604 0.00183 -0.0697 0.5057 0.9906
2.750 0.6436 0.00620 0.00192 -0.0714 0.4885 0.9944
3.000 0.6829 0.00634 0.00199 -0.0739 0.4717 0.9976
3.250 0.7209 0.00649 0.00206 -0.0762 0.4521 1.0000
3.500 0.7424 0.00663 0.00213 -0.0749 0.4338 1.0000
3.750 0.7641 0.00677 0.00222 -0.0736 0.4184 1.0000
4.000 0.7859 0.00691 0.00231 -0.0723 0.4025 1.0000
4.250 0.8071 0.00711 0.00242 -0.0709 0.3805 1.0000
4.500 0.8280 0.00732 0.00255 -0.0695 0.3590 1.0000
4.750 0.8490 0.00755 0.00269 -0.0681 0.3356 1.0000
5.000 0.8689 0.00785 0.00286 -0.0665 0.3068 1.0000
5.250 0.8888 0.00817 0.00305 -0.0649 0.2789 1.0000
5.500 0.9078 0.00855 0.00329 -0.0632 0.2461 1.0000
5.750 0.9255 0.00903 0.00356 -0.0613 0.2079 1.0000
6.000 0.9440 0.00946 0.00384 -0.0595 0.1766 1.0000
6.250 0.9626 0.00990 0.00414 -0.0578 0.1483 1.0000
6.500 0.9811 0.01036 0.00445 -0.0560 0.1224 1.0000
6.750 1.0002 0.01078 0.00477 -0.0544 0.1015 1.0000
7.000 1.0191 0.01121 0.00509 -0.0527 0.0845 1.0000
7.250 1.0386 0.01159 0.00542 -0.0512 0.0715 1.0000
7.500 1.0580 0.01199 0.00575 -0.0496 0.0611 1.0000
7.750 1.0778 0.01235 0.00608 -0.0482 0.0538 1.0000
8.000 1.0978 0.01270 0.00641 -0.0467 0.0476 1.0000
8.250 1.1169 0.01310 0.00678 -0.0452 0.0420 1.0000
8.500 1.1363 0.01347 0.00714 -0.0437 0.0379 1.0000
8.750 1.1552 0.01386 0.00753 -0.0421 0.0343 1.0000
9.000 1.1737 0.01426 0.00792 -0.0405 0.0312 1.0000
9.250 1.1912 0.01471 0.00838 -0.0387 0.0283 1.0000
9.500 1.2091 0.01511 0.00879 -0.0369 0.0263 1.0000
9.750 1.2212 0.01570 0.00939 -0.0342 0.0240 1.0000
10.000 1.2374 0.01605 0.00977 -0.0322 0.0230 1.0000
10.250 1.2523 0.01648 0.01024 -0.0300 0.0218 1.0000
10.500 1.2662 0.01698 0.01075 -0.0277 0.0208 1.0000
10.750 1.2755 0.01775 0.01157 -0.0248 0.0195 1.0000
11.000 1.2903 0.01825 0.01212 -0.0228 0.0192 1.0000
11.250 1.3047 0.01879 0.01270 -0.0208 0.0185 1.0000
11.500 1.3179 0.01940 0.01337 -0.0188 0.0180 1.0000
11.750 1.3307 0.02006 0.01407 -0.0168 0.0174 1.0000
12.000 1.3419 0.02083 0.01488 -0.0147 0.0170 1.0000
12.250 1.3505 0.02178 0.01588 -0.0125 0.0165 1.0000
12.500 1.3531 0.02315 0.01733 -0.0097 0.0160 1.0000
12.750 1.3625 0.02416 0.01840 -0.0078 0.0157 1.0000
13.000 1.3729 0.02512 0.01945 -0.0062 0.0155 1.0000
13.250 1.3835 0.02614 0.02053 -0.0048 0.0151 1.0000
13.500 1.3911 0.02740 0.02187 -0.0032 0.0149 1.0000
13.750 1.3984 0.02875 0.02330 -0.0019 0.0147 1.0000
14.000 1.4056 0.03018 0.02479 -0.0006 0.0143 1.0000
14.250 1.4113 0.03180 0.02648 0.0005 0.0141 1.0000
14.500 1.4165 0.03354 0.02829 0.0014 0.0139 1.0000
14.750 1.4193 0.03558 0.03041 0.0023 0.0137 1.0000
15.000 1.4217 0.03774 0.03265 0.0029 0.0135 1.0000
15.250 1.4191 0.04052 0.03552 0.0034 0.0133 1.0000
15.500 1.4163 0.04343 0.03851 0.0036 0.0131 1.0000
15.750 1.4107 0.04677 0.04196 0.0036 0.0129 1.0000
16.000 1.3951 0.05136 0.04668 0.0034 0.0127 1.0000
16.250 1.3974 0.05407 0.04949 0.0030 0.0126 1.0000
16.500 1.3979 0.05708 0.05259 0.0024 0.0125 1.0000
16.750 1.3927 0.06084 0.05646 0.0016 0.0124 1.0000
17.000 1.3917 0.06419 0.05991 0.0007 0.0123 1.0000
17.250 1.3855 0.06826 0.06408 -0.0004 0.0122 1.0000
17.500 1.3811 0.07222 0.06815 -0.0016 0.0120 1.0000
17.750 1.3721 0.07683 0.07287 -0.0031 0.0120 1.0000
18.000 1.3650 0.08128 0.07742 -0.0046 0.0119 1.0000
18.250 1.3551 0.08619 0.08244 -0.0064 0.0119 1.0000
18.500 1.3464 0.09110 0.08745 -0.0083 0.0117 1.0000
18.750 1.3361 0.09630 0.09275 -0.0104 0.0116 1.0000
19.000 1.3255 0.10164 0.09819 -0.0126 0.0116 1.0000
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