NACA 2418 (naca2418-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2418 (naca2418-il) Reynolds number: 50,000 Max Cl/Cd: 27.33 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2418-il-50000-n5.txt Download as CSV file: xf-naca2418-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2418
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
------ -------- --------- --------- -------- -------- --------
-12.500 -0.4996 0.10521 0.09626 -0.0490 1.0000 0.1228
-12.250 -0.6177 0.08014 0.07111 -0.0630 1.0000 0.1272
-12.000 -0.7343 0.06365 0.05429 -0.0702 1.0000 0.1271
-11.750 -0.7835 0.05837 0.04879 -0.0684 1.0000 0.1278
-11.500 -0.8231 0.05509 0.04531 -0.0637 1.0000 0.1287
-11.250 -0.8345 0.05343 0.04364 -0.0599 1.0000 0.1306
-11.000 -0.8308 0.05245 0.04273 -0.0572 1.0000 0.1332
-10.750 -0.8390 0.05086 0.04108 -0.0536 1.0000 0.1358
-10.500 -0.8519 0.04893 0.03897 -0.0494 1.0000 0.1385
-10.250 -0.8667 0.04676 0.03648 -0.0449 1.0000 0.1414
-10.000 -0.8578 0.04592 0.03575 -0.0425 1.0000 0.1446
-9.750 -0.8535 0.04492 0.03474 -0.0396 1.0000 0.1482
-9.500 -0.8542 0.04346 0.03309 -0.0363 1.0000 0.1524
-9.250 -0.8512 0.04212 0.03161 -0.0333 1.0000 0.1564
-9.000 -0.8415 0.04141 0.03097 -0.0309 1.0000 0.1605
-8.750 -0.8354 0.04032 0.02975 -0.0283 1.0000 0.1655
-8.500 -0.8281 0.03919 0.02847 -0.0258 1.0000 0.1705
-8.250 -0.8167 0.03856 0.02792 -0.0236 1.0000 0.1753
-8.000 -0.8074 0.03762 0.02682 -0.0213 1.0000 0.1814
-7.750 -0.7956 0.03686 0.02604 -0.0193 1.0000 0.1870
-7.500 -0.7831 0.03625 0.02543 -0.0174 1.0000 0.1932
-7.250 -0.7688 0.03543 0.02444 -0.0159 0.9994 0.2006
-7.000 -0.7331 0.03488 0.02394 -0.0182 0.9926 0.2101
-6.750 -0.6996 0.03418 0.02317 -0.0202 0.9851 0.2204
-6.500 -0.6648 0.03354 0.02235 -0.0223 0.9777 0.2329
-6.250 -0.6311 0.03304 0.02195 -0.0240 0.9697 0.2439
-6.000 -0.5980 0.03249 0.02137 -0.0256 0.9617 0.2567
-5.750 -0.5636 0.03196 0.02076 -0.0275 0.9537 0.2714
-5.500 -0.5329 0.03151 0.02032 -0.0285 0.9449 0.2857
-5.250 -0.4977 0.03107 0.01993 -0.0303 0.9372 0.3012
-5.000 -0.4686 0.03066 0.01954 -0.0309 0.9276 0.3167
-4.750 -0.4331 0.03027 0.01916 -0.0327 0.9199 0.3345
-4.500 -0.4051 0.02993 0.01883 -0.0330 0.9098 0.3517
-4.250 -0.3694 0.02957 0.01851 -0.0346 0.9020 0.3715
-4.000 -0.3420 0.02930 0.01828 -0.0348 0.8918 0.3904
-3.750 -0.3067 0.02898 0.01803 -0.0362 0.8837 0.4120
-3.500 -0.2789 0.02875 0.01787 -0.0362 0.8735 0.4331
-3.250 -0.2447 0.02847 0.01769 -0.0373 0.8652 0.4569
-3.000 -0.2154 0.02825 0.01756 -0.0375 0.8555 0.4808
-2.750 -0.1835 0.02800 0.01738 -0.0380 0.8464 0.5072
-2.500 -0.1541 0.02779 0.01725 -0.0380 0.8372 0.5339
-2.250 -0.1256 0.02760 0.01717 -0.0376 0.8272 0.5602
-2.000 -0.0951 0.02740 0.01705 -0.0376 0.8184 0.5888
-1.750 -0.0689 0.02727 0.01698 -0.0369 0.8078 0.6178
-1.500 -0.0363 0.02709 0.01690 -0.0369 0.7998 0.6464
-1.250 -0.0117 0.02706 0.01695 -0.0357 0.7885 0.6745
-1.000 0.0234 0.02686 0.01679 -0.0360 0.7814 0.7051
-0.750 0.0465 0.02698 0.01699 -0.0344 0.7691 0.7316
-0.500 0.0865 0.02679 0.01681 -0.0353 0.7629 0.7610
-0.250 0.1072 0.02702 0.01707 -0.0336 0.7497 0.7882
0.000 0.1516 0.02688 0.01692 -0.0352 0.7432 0.8139
0.250 0.1790 0.02719 0.01725 -0.0347 0.7304 0.8386
0.500 0.2272 0.02705 0.01704 -0.0373 0.7233 0.8621
0.750 0.2603 0.02737 0.01736 -0.0380 0.7106 0.8854
1.000 0.3142 0.02722 0.01711 -0.0418 0.7031 0.9055
1.250 0.3553 0.02752 0.01739 -0.0444 0.6902 0.9261
1.500 0.4169 0.02727 0.01703 -0.0499 0.6820 0.9421
1.750 0.4622 0.02750 0.01726 -0.0536 0.6684 0.9601
2.000 0.5150 0.02740 0.01710 -0.0584 0.6577 0.9754
2.250 0.5658 0.02730 0.01697 -0.0629 0.6455 0.9898
2.500 0.6053 0.02735 0.01699 -0.0658 0.6329 1.0000
2.750 0.6247 0.02722 0.01676 -0.0644 0.6232 1.0000
3.000 0.6320 0.02754 0.01707 -0.0614 0.6107 1.0000
3.250 0.6533 0.02744 0.01686 -0.0601 0.6011 1.0000
3.500 0.6611 0.02781 0.01723 -0.0570 0.5887 1.0000
3.750 0.6787 0.02791 0.01726 -0.0552 0.5785 1.0000
4.000 0.6924 0.02817 0.01748 -0.0529 0.5672 1.0000
4.250 0.7074 0.02844 0.01772 -0.0507 0.5567 1.0000
4.500 0.7251 0.02865 0.01789 -0.0488 0.5462 1.0000
4.750 0.7382 0.02906 0.01828 -0.0464 0.5354 1.0000
5.000 0.7587 0.02925 0.01841 -0.0450 0.5254 1.0000
5.250 0.7700 0.02978 0.01895 -0.0423 0.5145 1.0000
5.500 0.7929 0.02994 0.01904 -0.0412 0.5046 1.0000
5.750 0.8019 0.03059 0.01973 -0.0383 0.4934 1.0000
6.000 0.8276 0.03070 0.01977 -0.0375 0.4839 1.0000
6.250 0.8340 0.03148 0.02061 -0.0343 0.4722 1.0000
6.500 0.8616 0.03156 0.02059 -0.0338 0.4628 1.0000
6.750 0.8664 0.03242 0.02155 -0.0305 0.4508 1.0000
7.000 0.8868 0.03274 0.02184 -0.0291 0.4405 1.0000
7.250 0.8993 0.03333 0.02246 -0.0268 0.4290 1.0000
7.500 0.9119 0.03395 0.02309 -0.0245 0.4179 1.0000
7.750 0.9337 0.03416 0.02325 -0.0233 0.4071 1.0000
8.000 0.9377 0.03513 0.02429 -0.0201 0.3953 1.0000
8.250 0.9579 0.03541 0.02452 -0.0187 0.3848 1.0000
8.500 0.9629 0.03630 0.02546 -0.0157 0.3736 1.0000
8.750 0.9737 0.03700 0.02618 -0.0134 0.3632 1.0000
9.000 0.9873 0.03758 0.02674 -0.0114 0.3527 1.0000
9.250 0.9904 0.03876 0.02798 -0.0086 0.3424 1.0000
9.500 1.0116 0.03904 0.02819 -0.0074 0.3324 1.0000
9.750 1.0072 0.04075 0.03004 -0.0043 0.3221 1.0000
10.000 1.0263 0.04118 0.03038 -0.0031 0.3125 1.0000
10.250 1.0226 0.04303 0.03236 -0.0005 0.3024 1.0000
10.500 1.0353 0.04391 0.03321 0.0009 0.2930 1.0000
10.750 1.0359 0.04563 0.03503 0.0029 0.2832 1.0000
11.000 1.0421 0.04707 0.03648 0.0044 0.2741 1.0000
11.250 1.0468 0.04862 0.03806 0.0059 0.2647 1.0000
11.500 1.0467 0.05071 0.04022 0.0073 0.2559 1.0000
11.750 1.0549 0.05206 0.04156 0.0085 0.2470 1.0000
12.000 1.0493 0.05486 0.04447 0.0095 0.2386 1.0000
12.250 1.0589 0.05616 0.04574 0.0105 0.2303 1.0000
12.500 1.0496 0.05958 0.04928 0.0111 0.2224 1.0000
12.750 1.0561 0.06131 0.05100 0.0119 0.2147 1.0000
13.000 1.0475 0.06491 0.05471 0.0121 0.2075 1.0000
13.250 1.0437 0.06801 0.05789 0.0122 0.2003 1.0000
13.500 1.0447 0.07063 0.06054 0.0125 0.1938 1.0000
13.750 1.0202 0.07676 0.06688 0.0113 0.1872 1.0000
14.000 1.0461 0.07603 0.06599 0.0126 0.1811 1.0000
14.250 0.9792 0.08902 0.07941 0.0081 0.1750 1.0000
14.500 0.9941 0.08977 0.08012 0.0087 0.1694 1.0000
14.750 0.8870 0.11219 0.10285 -0.0011 0.1604 1.0000
15.000 0.9060 0.11208 0.10274 -0.0003 0.1563 1.0000
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