NACA 2.5411 (naca2411-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2.5411 (naca2411-il) Reynolds number: 500,000 Max Cl/Cd: 95.6 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2411-il-500000.txt Download as CSV file: xf-naca2411-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7556 0.05417 0.05117 -0.0700 1.0000 0.0217
-12.250 -0.7845 0.04684 0.04366 -0.0762 1.0000 0.0216
-12.000 -0.8126 0.04241 0.03906 -0.0770 1.0000 0.0215
-11.750 -0.8384 0.04004 0.03656 -0.0731 1.0000 0.0215
-11.500 -0.8584 0.03786 0.03420 -0.0684 1.0000 0.0215
-11.250 -0.8663 0.03634 0.03248 -0.0646 1.0000 0.0217
-11.000 -0.8774 0.03401 0.02991 -0.0605 1.0000 0.0218
-10.750 -0.8881 0.03105 0.02668 -0.0563 1.0000 0.0220
-10.500 -0.8881 0.02898 0.02445 -0.0530 1.0000 0.0223
-10.250 -0.8818 0.02757 0.02294 -0.0503 1.0000 0.0226
-10.000 -0.8726 0.02644 0.02170 -0.0478 1.0000 0.0229
-9.750 -0.8616 0.02546 0.02062 -0.0455 1.0000 0.0233
-9.500 -0.8379 0.02420 0.01919 -0.0458 0.9986 0.0238
-9.250 -0.8077 0.02302 0.01785 -0.0471 0.9962 0.0245
-9.000 -0.7762 0.02191 0.01656 -0.0486 0.9942 0.0253
-8.750 -0.7465 0.02103 0.01550 -0.0495 0.9913 0.0260
-8.500 -0.7172 0.01970 0.01397 -0.0505 0.9885 0.0266
-8.250 -0.6873 0.01831 0.01250 -0.0517 0.9861 0.0276
-8.000 -0.6535 0.01756 0.01170 -0.0533 0.9843 0.0284
-7.750 -0.6228 0.01691 0.01097 -0.0542 0.9813 0.0295
-7.500 -0.5924 0.01631 0.01029 -0.0549 0.9776 0.0307
-7.250 -0.5585 0.01580 0.00968 -0.0563 0.9750 0.0318
-7.000 -0.5257 0.01476 0.00862 -0.0577 0.9728 0.0336
-6.750 -0.4890 0.01424 0.00808 -0.0597 0.9713 0.0356
-6.500 -0.4610 0.01380 0.00757 -0.0597 0.9659 0.0375
-6.250 -0.4284 0.01304 0.00680 -0.0609 0.9623 0.0404
-6.000 -0.3914 0.01265 0.00639 -0.0628 0.9601 0.0442
-5.750 -0.3547 0.01207 0.00581 -0.0647 0.9585 0.0490
-5.500 -0.3162 0.01173 0.00545 -0.0670 0.9573 0.0541
-5.250 -0.2907 0.01127 0.00502 -0.0665 0.9511 0.0603
-5.000 -0.2573 0.01089 0.00464 -0.0676 0.9475 0.0675
-4.750 -0.2220 0.01057 0.00432 -0.0691 0.9447 0.0758
-4.500 -0.1866 0.01017 0.00396 -0.0707 0.9421 0.0872
-4.250 -0.1624 0.00987 0.00372 -0.0698 0.9341 0.0989
-4.000 -0.1301 0.00955 0.00344 -0.0706 0.9293 0.1151
-3.750 -0.1017 0.00925 0.00321 -0.0706 0.9227 0.1339
-3.500 -0.0735 0.00896 0.00300 -0.0706 0.9152 0.1565
-3.250 -0.0447 0.00869 0.00280 -0.0707 0.9080 0.1819
-3.000 -0.0176 0.00845 0.00264 -0.0704 0.8990 0.2098
-2.750 0.0093 0.00823 0.00250 -0.0701 0.8898 0.2408
-2.500 0.0373 0.00800 0.00235 -0.0700 0.8808 0.2745
-2.250 0.0625 0.00779 0.00225 -0.0693 0.8694 0.3107
-2.000 0.0887 0.00759 0.00214 -0.0688 0.8584 0.3512
-1.500 0.1384 0.00705 0.00195 -0.0673 0.8346 0.4749
-1.250 0.1611 0.00676 0.00191 -0.0661 0.8212 0.5620
-1.000 0.1834 0.00650 0.00188 -0.0647 0.8077 0.6454
-0.750 0.2054 0.00628 0.00187 -0.0632 0.7936 0.7212
-0.500 0.2280 0.00610 0.00188 -0.0616 0.7793 0.7935
-0.250 0.2533 0.00600 0.00192 -0.0606 0.7646 0.8601
0.000 0.2882 0.00602 0.00198 -0.0616 0.7493 0.9115
0.250 0.3285 0.00612 0.00204 -0.0639 0.7329 0.9411
0.500 0.3692 0.00626 0.00208 -0.0664 0.7157 0.9580
0.750 0.4073 0.00641 0.00214 -0.0684 0.6978 0.9705
1.000 0.4496 0.00656 0.00219 -0.0713 0.6795 0.9783
1.250 0.4896 0.00671 0.00223 -0.0738 0.6608 0.9860
1.500 0.5304 0.00685 0.00228 -0.0766 0.6419 0.9926
1.750 0.5728 0.00696 0.00230 -0.0798 0.6220 0.9982
2.000 0.6021 0.00707 0.00232 -0.0801 0.6041 1.0000
2.250 0.6229 0.00717 0.00235 -0.0787 0.5873 1.0000
2.500 0.6440 0.00728 0.00240 -0.0773 0.5716 1.0000
2.750 0.6653 0.00741 0.00246 -0.0759 0.5560 1.0000
3.000 0.6865 0.00755 0.00254 -0.0744 0.5400 1.0000
3.250 0.7078 0.00770 0.00263 -0.0730 0.5239 1.0000
3.500 0.7292 0.00785 0.00272 -0.0717 0.5082 1.0000
3.750 0.7506 0.00801 0.00284 -0.0703 0.4917 1.0000
4.000 0.7718 0.00819 0.00295 -0.0689 0.4742 1.0000
4.250 0.7931 0.00838 0.00308 -0.0675 0.4571 1.0000
4.500 0.8147 0.00856 0.00322 -0.0662 0.4405 1.0000
5.000 0.8575 0.00897 0.00352 -0.0635 0.4025 1.0000
5.250 0.8782 0.00922 0.00369 -0.0620 0.3791 1.0000
5.500 0.8985 0.00951 0.00389 -0.0605 0.3526 1.0000
5.750 0.9181 0.00984 0.00412 -0.0589 0.3240 1.0000
6.000 0.9368 0.01025 0.00438 -0.0571 0.2916 1.0000
6.250 0.9543 0.01074 0.00470 -0.0552 0.2553 1.0000
6.500 0.9712 0.01130 0.00506 -0.0533 0.2156 1.0000
6.750 0.9877 0.01189 0.00545 -0.0513 0.1796 1.0000
7.000 1.0044 0.01249 0.00588 -0.0493 0.1465 1.0000
7.250 1.0210 0.01308 0.00633 -0.0474 0.1189 1.0000
7.500 1.0374 0.01370 0.00681 -0.0454 0.0962 1.0000
7.750 1.0547 0.01424 0.00727 -0.0436 0.0804 1.0000
8.000 1.0718 0.01478 0.00776 -0.0418 0.0687 1.0000
8.250 1.0883 0.01535 0.00829 -0.0398 0.0600 1.0000
8.500 1.1048 0.01590 0.00881 -0.0379 0.0533 1.0000
8.750 1.1212 0.01642 0.00937 -0.0359 0.0482 1.0000
9.000 1.1335 0.01709 0.01000 -0.0333 0.0435 1.0000
9.250 1.1477 0.01759 0.01055 -0.0309 0.0401 1.0000
9.500 1.1602 0.01818 0.01115 -0.0284 0.0372 1.0000
9.750 1.1695 0.01896 0.01197 -0.0254 0.0346 1.0000
10.000 1.1832 0.01954 0.01260 -0.0233 0.0327 1.0000
10.250 1.1948 0.02025 0.01333 -0.0209 0.0309 1.0000
10.500 1.2002 0.02133 0.01444 -0.0178 0.0295 1.0000
10.750 1.2103 0.02219 0.01539 -0.0154 0.0284 1.0000
11.000 1.2212 0.02302 0.01629 -0.0133 0.0275 1.0000
11.250 1.2323 0.02386 0.01718 -0.0113 0.0263 1.0000
11.500 1.2412 0.02487 0.01824 -0.0093 0.0254 1.0000
11.750 1.2453 0.02626 0.01966 -0.0069 0.0246 1.0000
12.000 1.2457 0.02803 0.02150 -0.0044 0.0239 1.0000
12.250 1.2550 0.02920 0.02277 -0.0028 0.0235 1.0000
12.500 1.2628 0.03053 0.02420 -0.0012 0.0230 1.0000
12.750 1.2692 0.03203 0.02579 0.0003 0.0226 1.0000
13.000 1.2762 0.03352 0.02736 0.0015 0.0221 1.0000
13.250 1.2820 0.03517 0.02910 0.0027 0.0215 1.0000
13.500 1.2869 0.03696 0.03096 0.0038 0.0211 1.0000
13.750 1.2914 0.03885 0.03291 0.0047 0.0208 1.0000
14.000 1.2947 0.04091 0.03504 0.0055 0.0204 1.0000
14.250 1.2952 0.04333 0.03753 0.0064 0.0199 1.0000
14.500 1.2948 0.04597 0.04026 0.0072 0.0195 1.0000
14.750 1.2973 0.04833 0.04275 0.0076 0.0193 1.0000
15.000 1.2991 0.05081 0.04536 0.0078 0.0191 1.0000
15.250 1.2992 0.05359 0.04827 0.0079 0.0189 1.0000
15.500 1.2994 0.05643 0.05124 0.0077 0.0186 1.0000
15.750 1.2982 0.05949 0.05443 0.0074 0.0184 1.0000
16.000 1.2955 0.06286 0.05794 0.0069 0.0181 1.0000
16.250 1.2923 0.06640 0.06161 0.0062 0.0180 1.0000
16.500 1.2888 0.07008 0.06541 0.0051 0.0177 1.0000
16.750 1.2825 0.07425 0.06972 0.0040 0.0176 1.0000
17.000 1.2761 0.07858 0.07419 0.0024 0.0174 1.0000
17.250 1.2686 0.08322 0.07896 0.0007 0.0173 1.0000
17.500 1.2610 0.08798 0.08384 -0.0014 0.0171 1.0000
17.750 1.2511 0.09324 0.08923 -0.0037 0.0170 1.0000
18.000 1.2436 0.09826 0.09435 -0.0062 0.0168 1.0000
18.250 1.2284 0.10482 0.10110 -0.0094 0.0169 1.0000
18.500 1.2162 0.11099 0.10740 -0.0127 0.0167 1.0000
18.750 1.2059 0.11696 0.11347 -0.0160 0.0166 1.0000
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Polar data table (+)
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