NACA 2408 (naca2408-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2408 (naca2408-il) Reynolds number: 200,000 Max Cl/Cd: 58.86 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2408-il-200000-n5.txt Download as CSV file: xf-naca2408-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2408
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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5597 0.08283 0.07932 -0.0182 1.0000 0.0149
-8.750 -0.5671 0.07690 0.07345 -0.0223 1.0000 0.0148
-8.500 -0.5762 0.06961 0.06622 -0.0293 1.0000 0.0147
-8.250 -0.5855 0.05851 0.05507 -0.0397 1.0000 0.0145
-8.000 -0.6101 0.04154 0.03752 -0.0473 1.0000 0.0142
-7.750 -0.6123 0.03383 0.02910 -0.0477 1.0000 0.0146
-7.500 -0.6017 0.02975 0.02447 -0.0468 1.0000 0.0155
-7.250 -0.5866 0.02671 0.02087 -0.0458 1.0000 0.0167
-7.000 -0.5696 0.02406 0.01775 -0.0446 1.0000 0.0176
-6.750 -0.5506 0.02231 0.01575 -0.0437 1.0000 0.0186
-6.500 -0.5297 0.02128 0.01456 -0.0428 1.0000 0.0198
-6.250 -0.5082 0.02036 0.01345 -0.0418 1.0000 0.0217
-6.000 -0.4861 0.01936 0.01219 -0.0409 1.0000 0.0241
-5.750 -0.4637 0.01836 0.01095 -0.0399 1.0000 0.0258
-5.500 -0.4419 0.01727 0.00981 -0.0391 1.0000 0.0284
-5.250 -0.4191 0.01678 0.00923 -0.0384 1.0000 0.0318
-5.000 -0.3958 0.01617 0.00843 -0.0375 1.0000 0.0347
-4.750 -0.3724 0.01535 0.00758 -0.0370 0.9999 0.0382
-4.500 -0.3368 0.01482 0.00698 -0.0389 0.9963 0.0426
-4.250 -0.3011 0.01439 0.00641 -0.0407 0.9924 0.0464
-4.000 -0.2660 0.01367 0.00567 -0.0425 0.9882 0.0507
-3.750 -0.2304 0.01324 0.00519 -0.0443 0.9840 0.0557
-3.500 -0.1958 0.01281 0.00470 -0.0458 0.9790 0.0609
-3.250 -0.1595 0.01239 0.00427 -0.0477 0.9752 0.0701
-3.000 -0.1266 0.01200 0.00392 -0.0488 0.9690 0.0868
-2.750 -0.0909 0.01158 0.00363 -0.0507 0.9646 0.1190
-2.500 -0.0597 0.01124 0.00340 -0.0515 0.9572 0.1587
-2.250 -0.0255 0.01084 0.00322 -0.0530 0.9515 0.2144
-2.000 0.0043 0.01045 0.00308 -0.0536 0.9426 0.2814
-1.750 0.0365 0.00991 0.00293 -0.0547 0.9358 0.3866
-1.500 0.0633 0.00927 0.00286 -0.0546 0.9255 0.5327
-1.250 0.0889 0.00871 0.00283 -0.0538 0.9153 0.6785
-1.000 0.1142 0.00831 0.00280 -0.0525 0.9051 0.7987
-0.750 0.1493 0.00810 0.00277 -0.0530 0.8953 0.9166
-0.500 0.1970 0.00801 0.00264 -0.0570 0.8850 0.9878
-0.250 0.2306 0.00797 0.00251 -0.0580 0.8710 1.0000
0.000 0.2579 0.00797 0.00242 -0.0577 0.8549 1.0000
0.250 0.2849 0.00798 0.00234 -0.0573 0.8380 1.0000
0.500 0.3114 0.00801 0.00229 -0.0568 0.8196 1.0000
0.750 0.3377 0.00807 0.00225 -0.0562 0.8001 1.0000
1.000 0.3639 0.00814 0.00224 -0.0556 0.7800 1.0000
1.250 0.3899 0.00823 0.00224 -0.0550 0.7584 1.0000
1.500 0.4159 0.00834 0.00226 -0.0544 0.7362 1.0000
1.750 0.4415 0.00848 0.00230 -0.0538 0.7101 1.0000
2.000 0.4664 0.00867 0.00233 -0.0529 0.6749 1.0000
2.250 0.4907 0.00892 0.00237 -0.0520 0.6333 1.0000
2.500 0.5153 0.00917 0.00247 -0.0512 0.5941 1.0000
2.750 0.5400 0.00945 0.00258 -0.0504 0.5585 1.0000
3.000 0.5643 0.00977 0.00272 -0.0497 0.5164 1.0000
3.250 0.5886 0.01011 0.00290 -0.0490 0.4731 1.0000
3.500 0.6133 0.01044 0.00309 -0.0484 0.4330 1.0000
3.750 0.6375 0.01083 0.00331 -0.0477 0.3865 1.0000
4.000 0.6617 0.01125 0.00358 -0.0471 0.3394 1.0000
4.250 0.6840 0.01194 0.00392 -0.0464 0.2626 1.0000
4.500 0.7049 0.01291 0.00440 -0.0455 0.1688 1.0000
4.750 0.7269 0.01375 0.00493 -0.0449 0.1042 1.0000
5.000 0.7501 0.01445 0.00548 -0.0442 0.0700 1.0000
5.250 0.7742 0.01501 0.00601 -0.0436 0.0549 1.0000
5.500 0.7982 0.01559 0.00657 -0.0430 0.0486 1.0000
5.750 0.8224 0.01611 0.00719 -0.0424 0.0458 1.0000
6.000 0.8461 0.01669 0.00788 -0.0418 0.0426 1.0000
6.250 0.8685 0.01744 0.00867 -0.0410 0.0394 1.0000
6.500 0.8899 0.01833 0.00963 -0.0400 0.0371 1.0000
6.750 0.9127 0.01900 0.01042 -0.0393 0.0348 1.0000
7.000 0.9346 0.01981 0.01134 -0.0384 0.0325 1.0000
7.250 0.9557 0.02071 0.01230 -0.0375 0.0298 1.0000
7.500 0.9726 0.02244 0.01408 -0.0361 0.0269 1.0000
7.750 0.9953 0.02316 0.01498 -0.0353 0.0254 1.0000
8.000 1.0170 0.02404 0.01602 -0.0344 0.0229 1.0000
8.250 1.0377 0.02506 0.01716 -0.0335 0.0208 1.0000
8.500 1.0573 0.02623 0.01840 -0.0325 0.0193 1.0000
8.750 1.0738 0.02825 0.02050 -0.0313 0.0178 1.0000
9.000 1.0940 0.02928 0.02179 -0.0302 0.0165 1.0000
9.250 1.1123 0.03074 0.02354 -0.0290 0.0151 1.0000
9.500 1.1286 0.03247 0.02551 -0.0276 0.0142 1.0000
9.750 1.1435 0.03414 0.02740 -0.0262 0.0135 1.0000
10.000 1.1570 0.03576 0.02920 -0.0248 0.0129 1.0000
10.250 1.1684 0.03737 0.03096 -0.0233 0.0124 1.0000
10.500 1.1721 0.04014 0.03397 -0.0212 0.0118 1.0000
10.750 1.1749 0.04271 0.03692 -0.0188 0.0114 1.0000
11.000 1.1702 0.04552 0.04009 -0.0158 0.0110 1.0000
11.250 1.1610 0.04870 0.04359 -0.0132 0.0107 1.0000
11.500 1.1478 0.05237 0.04756 -0.0113 0.0105 1.0000
11.750 1.1315 0.05670 0.05217 -0.0106 0.0104 1.0000
12.000 1.1128 0.06183 0.05756 -0.0115 0.0103 1.0000
12.250 1.0922 0.06794 0.06393 -0.0140 0.0103 1.0000
12.500 1.0699 0.07529 0.07149 -0.0183 0.0104 1.0000
12.750 1.0458 0.08410 0.08050 -0.0243 0.0105 1.0000
13.000 1.0195 0.09465 0.09121 -0.0317 0.0108 1.0000
13.250 0.9916 0.10681 0.10347 -0.0397 0.0112 1.0000
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Polar data table (+)
Polar graphs
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