NACA 1408 (naca1408-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 1408 (naca1408-il) Reynolds number: 50,000 Max Cl/Cd: 32.33 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca1408-il-50000.txt Download as CSV file: xf-naca1408-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 1408
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4807 0.12855 0.12170 0.0043 1.0000 0.2213
-10.500 -0.4586 0.12283 0.11595 0.0052 1.0000 0.2309
-10.250 -0.4821 0.12198 0.11518 0.0035 1.0000 0.2361
-10.000 -0.4657 0.11711 0.11030 0.0044 1.0000 0.2494
-9.750 -0.4539 0.11270 0.10589 0.0049 1.0000 0.2607
-9.500 -0.4536 0.10908 0.10228 0.0048 1.0000 0.2695
-9.250 -0.4698 0.10717 0.10046 0.0040 1.0000 0.2795
-9.000 -0.4507 0.10210 0.09534 0.0049 1.0000 0.2912
-8.750 -0.4457 0.09806 0.09132 0.0051 1.0000 0.3009
-8.500 -0.4481 0.09453 0.08784 0.0051 1.0000 0.3125
-8.250 -0.4434 0.09079 0.08412 0.0058 1.0000 0.3278
-8.000 -0.4373 0.08705 0.08040 0.0066 1.0000 0.3448
-7.750 -0.4339 0.08333 0.07671 0.0073 1.0000 0.3602
-7.500 -0.5681 0.09125 0.08444 0.0163 1.0000 0.3540
-7.250 -0.5465 0.08706 0.08021 0.0184 1.0000 0.3768
-7.000 -0.5518 0.08439 0.07764 0.0194 1.0000 0.3985
-6.750 -0.5352 0.08041 0.07363 0.0207 1.0000 0.4175
-6.500 -0.5765 0.06759 0.06084 -0.0090 1.0000 0.2610
-6.250 -0.5733 0.04968 0.04162 -0.0277 1.0000 0.1457
-6.000 -0.5578 0.04519 0.03671 -0.0280 1.0000 0.1443
-5.750 -0.5402 0.04110 0.03211 -0.0279 1.0000 0.1440
-5.500 -0.5201 0.03725 0.02769 -0.0274 1.0000 0.1428
-5.250 -0.4982 0.03417 0.02404 -0.0267 1.0000 0.1456
-5.000 -0.4756 0.03156 0.02099 -0.0259 1.0000 0.1525
-4.750 -0.4512 0.02926 0.01843 -0.0250 1.0000 0.1585
-4.500 -0.4262 0.02715 0.01600 -0.0241 1.0000 0.1675
-4.250 -0.4017 0.02546 0.01422 -0.0232 1.0000 0.1830
-4.000 -0.3758 0.02371 0.01240 -0.0222 1.0000 0.2006
-3.750 -0.3502 0.02210 0.01084 -0.0212 1.0000 0.2363
-3.500 -0.3262 0.02006 0.00942 -0.0200 1.0000 0.3195
-3.250 -0.3137 0.01759 0.00857 -0.0162 1.0000 0.5378
-3.000 -0.3058 0.01655 0.00876 -0.0075 1.0000 0.7952
-2.750 -0.1494 0.01674 0.00780 -0.0280 1.0000 1.0000
-2.500 -0.1402 0.01627 0.00710 -0.0263 1.0000 1.0000
-2.250 -0.1289 0.01597 0.00660 -0.0244 1.0000 1.0000
-2.000 -0.1161 0.01578 0.00621 -0.0224 1.0000 1.0000
-1.750 -0.1020 0.01565 0.00590 -0.0205 1.0000 1.0000
-1.500 -0.0869 0.01558 0.00566 -0.0186 1.0000 1.0000
-1.250 -0.0705 0.01555 0.00545 -0.0170 1.0000 1.0000
-1.000 -0.0532 0.01556 0.00532 -0.0155 1.0000 1.0000
-0.750 -0.0351 0.01560 0.00524 -0.0141 1.0000 1.0000
-0.500 -0.0164 0.01568 0.00522 -0.0129 1.0000 1.0000
-0.250 0.0028 0.01579 0.00523 -0.0117 1.0000 1.0000
0.000 0.0223 0.01594 0.00531 -0.0108 1.0000 1.0000
0.250 0.0420 0.01612 0.00544 -0.0099 1.0000 1.0000
0.500 0.0618 0.01635 0.00563 -0.0091 1.0000 1.0000
0.750 0.0815 0.01662 0.00588 -0.0084 1.0000 1.0000
1.000 0.1012 0.01695 0.00620 -0.0078 1.0000 1.0000
1.250 0.1206 0.01733 0.00660 -0.0073 1.0000 1.0000
1.500 0.1396 0.01779 0.00708 -0.0070 1.0000 1.0000
1.750 0.1583 0.01833 0.00766 -0.0068 1.0000 1.0000
2.000 0.1765 0.01896 0.00836 -0.0068 1.0000 1.0000
2.250 0.1941 0.01969 0.00915 -0.0069 1.0000 1.0000
2.500 0.2112 0.02054 0.01008 -0.0072 1.0000 1.0000
2.750 0.2599 0.02168 0.01142 -0.0136 0.9855 1.0000
3.000 0.3377 0.02271 0.01278 -0.0245 0.9537 1.0000
3.250 0.4088 0.02324 0.01372 -0.0329 0.9176 1.0000
3.500 0.4836 0.02310 0.01406 -0.0403 0.8786 1.0000
3.750 0.5427 0.02236 0.01379 -0.0427 0.8355 1.0000
4.000 0.5831 0.02131 0.01303 -0.0403 0.7852 1.0000
4.250 0.6080 0.02029 0.01209 -0.0347 0.7249 1.0000
4.500 0.6237 0.01967 0.01132 -0.0281 0.6457 1.0000
4.750 0.6369 0.01970 0.01103 -0.0224 0.5406 1.0000
5.000 0.6411 0.02149 0.01137 -0.0162 0.3286 1.0000
5.250 0.6581 0.02429 0.01310 -0.0140 0.2186 1.0000
5.500 0.6846 0.02650 0.01497 -0.0130 0.1862 1.0000
5.750 0.7112 0.02842 0.01696 -0.0122 0.1651 1.0000
6.000 0.7383 0.03063 0.01931 -0.0115 0.1525 1.0000
6.250 0.7650 0.03321 0.02191 -0.0109 0.1440 1.0000
6.500 0.7884 0.03552 0.02469 -0.0098 0.1350 1.0000
6.750 0.8122 0.03876 0.02805 -0.0091 0.1303 1.0000
7.000 0.8314 0.04210 0.03211 -0.0077 0.1282 1.0000
7.250 0.8469 0.04564 0.03628 -0.0064 0.1248 1.0000
7.500 0.8598 0.04977 0.04099 -0.0053 0.1239 1.0000
7.750 0.8688 0.05471 0.04646 -0.0044 0.1265 1.0000
8.000 0.8782 0.05981 0.05187 -0.0038 0.1292 1.0000
8.250 0.8649 0.06693 0.05974 -0.0045 0.1385 1.0000
8.500 0.8698 0.07269 0.06563 -0.0048 0.1434 1.0000
8.750 0.8202 0.08401 0.07732 -0.0129 0.1668 1.0000
9.000 0.7159 0.10972 0.10273 -0.0492 0.3485 1.0000
9.250 0.7223 0.11443 0.10743 -0.0495 0.3427 1.0000
9.500 0.7361 0.11905 0.11210 -0.0488 0.3296 1.0000
9.750 0.7463 0.12339 0.11647 -0.0481 0.3157 1.0000
10.000 0.5712 0.11706 0.11029 -0.0328 0.3195 1.0000
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Polar data table (+)
Polar graphs
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