NACA 2408 (naca2408-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 2408 (naca2408-il) Reynolds number: 100,000 Max Cl/Cd: 52.56 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca2408-il-100000.txt Download as CSV file: xf-naca2408-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5135 0.10721 0.10220 -0.0076 1.0000 0.0961
-9.000 -0.5237 0.10425 0.09932 -0.0131 1.0000 0.0997
-8.750 -0.5419 0.10124 0.09645 -0.0214 1.0000 0.1006
-8.500 -0.5137 0.09567 0.09081 -0.0139 1.0000 0.1041
-8.250 -0.5070 0.09235 0.08748 -0.0140 1.0000 0.1084
-8.000 -0.5151 0.08887 0.08410 -0.0185 1.0000 0.1130
-7.750 -0.5300 0.08310 0.07837 -0.0323 1.0000 0.1155
-7.500 -0.5067 0.08095 0.07625 -0.0211 1.0000 0.1215
-7.250 -0.5148 0.07577 0.07098 -0.0341 1.0000 0.1289
-7.000 -0.5012 0.07229 0.06763 -0.0282 1.0000 0.1336
-6.500 -0.4890 0.06430 0.05958 -0.0321 1.0000 0.1481
-6.250 -0.4842 0.06007 0.05519 -0.0357 1.0000 0.1599
-6.000 -0.4711 0.04447 0.03810 -0.0437 1.0000 0.0866
-5.750 -0.4562 0.03954 0.03328 -0.0430 1.0000 0.0827
-5.500 -0.4397 0.03517 0.02840 -0.0425 1.0000 0.0820
-5.250 -0.4206 0.03115 0.02381 -0.0417 1.0000 0.0812
-5.000 -0.3992 0.02798 0.02005 -0.0407 1.0000 0.0827
-4.750 -0.3764 0.02567 0.01707 -0.0397 1.0000 0.0876
-4.500 -0.3536 0.02356 0.01484 -0.0390 1.0000 0.0918
-4.250 -0.3298 0.02244 0.01333 -0.0381 1.0000 0.0999
-4.000 -0.3054 0.02070 0.01149 -0.0375 1.0000 0.1049
-3.750 -0.2809 0.01972 0.01034 -0.0367 1.0000 0.1127
-3.500 -0.2563 0.01860 0.00922 -0.0362 1.0000 0.1212
-3.250 -0.2308 0.01762 0.00814 -0.0355 1.0000 0.1304
-3.000 -0.2059 0.01665 0.00727 -0.0350 1.0000 0.1461
-2.750 -0.1806 0.01568 0.00656 -0.0346 1.0000 0.1806
-2.500 -0.1548 0.01448 0.00601 -0.0347 1.0000 0.2896
-2.250 -0.1299 0.01317 0.00575 -0.0345 1.0000 0.4985
-2.000 -0.1144 0.01207 0.00590 -0.0301 1.0000 0.8381
-1.750 -0.0790 0.01196 0.00565 -0.0315 1.0000 1.0000
-1.500 -0.0566 0.01210 0.00555 -0.0310 1.0000 1.0000
-1.250 -0.0341 0.01227 0.00550 -0.0306 1.0000 1.0000
-1.000 -0.0117 0.01248 0.00554 -0.0302 1.0000 1.0000
-0.750 0.0106 0.01272 0.00565 -0.0299 1.0000 1.0000
-0.500 0.0327 0.01301 0.00581 -0.0296 1.0000 1.0000
-0.250 0.0545 0.01336 0.00605 -0.0294 1.0000 1.0000
0.000 0.0852 0.01375 0.00636 -0.0310 0.9968 1.0000
0.250 0.1380 0.01415 0.00666 -0.0367 0.9865 1.0000
0.500 0.1893 0.01445 0.00691 -0.0420 0.9749 1.0000
0.750 0.2379 0.01467 0.00711 -0.0465 0.9616 1.0000
1.000 0.2865 0.01480 0.00725 -0.0509 0.9484 1.0000
1.250 0.3380 0.01483 0.00732 -0.0556 0.9363 1.0000
1.500 0.3850 0.01477 0.00732 -0.0593 0.9224 1.0000
1.750 0.4285 0.01465 0.00727 -0.0619 0.9078 1.0000
2.000 0.4643 0.01455 0.00724 -0.0629 0.8897 1.0000
2.250 0.4993 0.01440 0.00717 -0.0635 0.8716 1.0000
2.500 0.5328 0.01421 0.00706 -0.0636 0.8535 1.0000
2.750 0.5618 0.01410 0.00701 -0.0629 0.8329 1.0000
3.000 0.5895 0.01392 0.00687 -0.0615 0.8098 1.0000
3.250 0.6142 0.01373 0.00669 -0.0594 0.7806 1.0000
3.500 0.6373 0.01360 0.00652 -0.0570 0.7463 1.0000
3.750 0.6604 0.01358 0.00645 -0.0549 0.7102 1.0000
4.000 0.6837 0.01366 0.00649 -0.0530 0.6743 1.0000
4.250 0.7066 0.01382 0.00658 -0.0512 0.6351 1.0000
4.500 0.7298 0.01406 0.00679 -0.0498 0.5972 1.0000
4.750 0.7518 0.01434 0.00699 -0.0480 0.5503 1.0000
5.000 0.7731 0.01471 0.00728 -0.0463 0.4959 1.0000
5.250 0.7906 0.01535 0.00757 -0.0439 0.3945 1.0000
5.500 0.7946 0.01819 0.00873 -0.0405 0.1565 1.0000
5.750 0.8114 0.01993 0.01016 -0.0386 0.1195 1.0000
6.000 0.8309 0.02131 0.01148 -0.0370 0.1070 1.0000
6.250 0.8517 0.02287 0.01296 -0.0357 0.0990 1.0000
6.500 0.8747 0.02418 0.01426 -0.0348 0.0900 1.0000
6.750 0.8998 0.02612 0.01622 -0.0340 0.0848 1.0000
7.000 0.9243 0.02763 0.01790 -0.0332 0.0780 1.0000
7.250 0.9496 0.03045 0.02070 -0.0328 0.0730 1.0000
7.500 0.9728 0.03232 0.02303 -0.0315 0.0686 1.0000
7.750 0.9949 0.03450 0.02544 -0.0305 0.0640 1.0000
8.000 1.0156 0.03789 0.02907 -0.0296 0.0618 1.0000
8.250 1.0301 0.04185 0.03353 -0.0279 0.0599 1.0000
8.500 1.0421 0.04500 0.03730 -0.0256 0.0585 1.0000
8.750 1.0512 0.04949 0.04226 -0.0236 0.0590 1.0000
9.000 1.0586 0.05506 0.04814 -0.0221 0.0602 1.0000
9.250 1.0424 0.06092 0.05514 -0.0180 0.0680 1.0000
9.500 0.9576 0.05509 0.04989 -0.0081 0.0687 1.0000
9.750 0.9629 0.06137 0.05625 -0.0072 0.0749 1.0000
10.000 0.9130 0.06549 0.06074 -0.0036 0.0766 1.0000
10.250 0.8763 0.07064 0.06605 -0.0034 0.0771 1.0000
10.500 0.8398 0.07699 0.07251 -0.0056 0.0772 1.0000
10.750 0.7732 0.09236 0.08795 -0.0156 0.0904 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 2408 (naca2408-il)